Griffith 30% Suction Airfoil (griffith30symsuction-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Griffith 30% Suction Airfoil (griffith30symsuction-il) Reynolds number: 1,000,000 Max Cl/Cd: 15.27 at α=13.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-griffith30symsuction-il-1000000-n5.txt Download as CSV file: xf-griffith30symsuction-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Griffith 30% Suction Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0209 0.08469 0.07888 -0.0588 0.7661 0.0171
-19.500 -1.0134 0.08247 0.07661 -0.0599 0.7658 0.0178
-19.250 -1.0032 0.08059 0.07470 -0.0610 0.7655 0.0187
-19.000 -0.9943 0.07864 0.07272 -0.0618 0.7652 0.0198
-18.750 -0.9865 0.07662 0.07066 -0.0625 0.7649 0.0211
-18.500 -0.9754 0.07497 0.06898 -0.0633 0.7647 0.0224
-18.250 -0.9655 0.07326 0.06725 -0.0639 0.7644 0.0243
-18.000 -0.9560 0.07153 0.06550 -0.0644 0.7642 0.0261
-17.750 -0.9468 0.06981 0.06377 -0.0648 0.7640 0.0289
-17.500 -0.9363 0.06826 0.06221 -0.0652 0.7638 0.0324
-17.250 -0.9272 0.06665 0.06060 -0.0654 0.7635 0.0369
-17.000 -0.9202 0.06489 0.05886 -0.0653 0.7633 0.0427
-16.750 -0.9100 0.06345 0.05745 -0.0653 0.7630 0.0495
-16.500 -0.8984 0.06213 0.05615 -0.0655 0.7628 0.0560
-16.250 -0.8862 0.06085 0.05489 -0.0657 0.7626 0.0619
-16.000 -0.8743 0.05955 0.05360 -0.0659 0.7625 0.0674
-15.750 -0.8609 0.05842 0.05248 -0.0660 0.7623 0.0727
-15.500 -0.8455 0.05745 0.05151 -0.0663 0.7621 0.0777
-15.250 -0.8318 0.05639 0.05048 -0.0664 0.7619 0.0835
-15.000 -0.8181 0.05533 0.04944 -0.0665 0.7618 0.0895
-14.750 -0.8051 0.05423 0.04835 -0.0665 0.7616 0.0965
-14.500 -0.7925 0.05316 0.04733 -0.0663 0.7615 0.1069
-14.000 -0.7699 0.05093 0.04529 -0.0656 0.7612 0.1369
-13.750 -0.7589 0.04982 0.04426 -0.0652 0.7610 0.1526
-13.500 -0.7436 0.04899 0.04347 -0.0652 0.7609 0.1633
-13.250 -0.7275 0.04822 0.04275 -0.0652 0.7607 0.1722
-13.000 -0.7093 0.04759 0.04214 -0.0654 0.7606 0.1807
-12.750 -0.6936 0.04682 0.04142 -0.0653 0.7605 0.1905
-12.500 -0.6755 0.04619 0.04081 -0.0654 0.7604 0.1984
-12.250 -0.6578 0.04555 0.04016 -0.0655 0.7602 0.2041
-12.000 -0.6403 0.04493 0.03956 -0.0655 0.7601 0.2096
-11.750 -0.6207 0.04443 0.03907 -0.0658 0.7600 0.2136
-11.500 -0.6003 0.04399 0.03861 -0.0660 0.7599 0.2167
-11.250 -0.5795 0.04358 0.03818 -0.0664 0.7598 0.2194
-11.000 -0.5425 0.04416 0.03880 -0.0722 0.7566 0.2252
-10.750 -0.5231 0.04379 0.03847 -0.0729 0.7557 0.2320
-10.500 -0.5039 0.04342 0.03810 -0.0733 0.7550 0.2371
-10.250 -0.4836 0.04307 0.03775 -0.0737 0.7544 0.2413
-10.000 -0.4650 0.04264 0.03734 -0.0737 0.7538 0.2482
-9.750 -0.4484 0.04216 0.03689 -0.0734 0.7533 0.2569
-9.500 -0.4304 0.04175 0.03650 -0.0732 0.7529 0.2649
-9.250 -0.4162 0.04116 0.03597 -0.0725 0.7525 0.2773
-9.000 -0.4018 0.04051 0.03536 -0.0717 0.7521 0.2896
-8.750 -0.3908 0.03968 0.03462 -0.0703 0.7517 0.3099
-8.500 -0.3820 0.03874 0.03380 -0.0686 0.7513 0.3369
-8.250 -0.3732 0.03780 0.03296 -0.0667 0.7509 0.3626
-8.000 -0.3646 0.03688 0.03212 -0.0649 0.7506 0.3831
-7.750 -0.3523 0.03621 0.03151 -0.0636 0.7503 0.3985
-7.500 -0.3362 0.03570 0.03103 -0.0627 0.7501 0.4120
-7.250 -0.3258 0.03495 0.03035 -0.0610 0.7498 0.4286
-7.000 -0.3235 0.03570 0.03118 -0.0595 0.7445 0.4439
-6.750 -0.3237 0.03500 0.03057 -0.0561 0.7431 0.4657
-6.500 -0.3390 0.03373 0.02950 -0.0501 0.7419 0.5060
-6.250 -0.3671 0.03204 0.02809 -0.0417 0.7408 0.5624
-6.000 -0.3604 0.03148 0.02762 -0.0389 0.7403 0.5872
-5.750 -0.3450 0.03115 0.02733 -0.0375 0.7398 0.6006
-5.500 -0.3289 0.03079 0.02700 -0.0363 0.7395 0.6126
-5.250 -0.3596 0.03155 0.02778 -0.0266 0.7328 0.6189
-5.000 -0.3537 0.03156 0.02782 -0.0231 0.7310 0.6268
-4.750 -0.3484 0.03113 0.02739 -0.0197 0.7299 0.6337
-4.500 -0.3313 0.03098 0.02724 -0.0184 0.7292 0.6384
-4.250 -0.3046 0.03110 0.02739 -0.0189 0.7287 0.6429
-4.000 -0.2848 0.03095 0.02724 -0.0181 0.7283 0.6481
-3.750 -0.3199 0.03108 0.02738 -0.0073 0.7220 0.6544
-3.500 -0.2967 0.03150 0.02781 -0.0071 0.7199 0.6572
-3.250 -0.2692 0.03175 0.02808 -0.0077 0.7189 0.6599
-3.000 -0.2438 0.03186 0.02820 -0.0080 0.7180 0.6638
-2.750 -0.2288 0.03155 0.02790 -0.0064 0.7171 0.6693
-2.500 -0.2059 0.03149 0.02783 -0.0062 0.7165 0.6725
-2.250 -0.1730 0.03174 0.02810 -0.0077 0.7161 0.6743
-2.000 -0.1423 0.03190 0.02827 -0.0089 0.7157 0.6762
-1.750 -0.1143 0.03194 0.02831 -0.0096 0.7152 0.6780
-0.250 -0.0003 0.03294 0.02935 -0.0042 0.7023 0.6922
0.750 0.0611 0.03278 0.02918 0.0020 0.6896 0.7038
1.000 0.0904 0.03260 0.02900 0.0010 0.6884 0.7046
1.250 0.1200 0.03237 0.02876 0.0000 0.6873 0.7055
1.750 0.1323 0.03243 0.02881 0.0064 0.6785 0.7119
2.000 0.1423 0.03190 0.02827 0.0089 0.6762 0.7157
2.250 0.1729 0.03174 0.02810 0.0078 0.6743 0.7161
2.500 0.2058 0.03149 0.02783 0.0062 0.6725 0.7165
2.750 0.2289 0.03155 0.02789 0.0064 0.6693 0.7172
3.000 0.2438 0.03185 0.02820 0.0080 0.6638 0.7180
3.250 0.2692 0.03174 0.02807 0.0077 0.6599 0.7189
3.500 0.2965 0.03149 0.02781 0.0072 0.6572 0.7200
3.750 0.3189 0.03106 0.02735 0.0075 0.6545 0.7221
4.000 0.2849 0.03094 0.02723 0.0181 0.6481 0.7283
4.250 0.3046 0.03109 0.02738 0.0189 0.6429 0.7287
4.500 0.3313 0.03097 0.02723 0.0185 0.6384 0.7292
4.750 0.3484 0.03112 0.02738 0.0197 0.6337 0.7299
5.000 0.3535 0.03154 0.02781 0.0232 0.6270 0.7310
5.250 0.3581 0.03153 0.02777 0.0269 0.6191 0.7329
5.500 0.3293 0.03078 0.02698 0.0362 0.6127 0.7395
5.750 0.3453 0.03114 0.02731 0.0375 0.6006 0.7399
6.000 0.3607 0.03147 0.02761 0.0388 0.5872 0.7403
6.250 0.3673 0.03203 0.02807 0.0416 0.5623 0.7408
6.500 0.3389 0.03373 0.02950 0.0501 0.5053 0.7419
6.750 0.3238 0.03500 0.03056 0.0561 0.4653 0.7431
7.000 0.3237 0.03569 0.03117 0.0594 0.4435 0.7446
7.250 0.3265 0.03495 0.03034 0.0608 0.4282 0.7498
7.500 0.3371 0.03569 0.03101 0.0625 0.4119 0.7501
7.750 0.3533 0.03620 0.03149 0.0634 0.3983 0.7503
8.000 0.3657 0.03686 0.03210 0.0647 0.3829 0.7506
8.250 0.3743 0.03778 0.03294 0.0665 0.3624 0.7509
8.500 0.3832 0.03872 0.03377 0.0683 0.3366 0.7513
8.750 0.3920 0.03966 0.03459 0.0701 0.3097 0.7517
9.000 0.4032 0.04048 0.03533 0.0714 0.2894 0.7521
9.250 0.4178 0.04112 0.03593 0.0722 0.2775 0.7525
9.500 0.4321 0.04171 0.03646 0.0729 0.2651 0.7529
9.750 0.4500 0.04213 0.03686 0.0731 0.2569 0.7533
10.000 0.4667 0.04262 0.03731 0.0733 0.2480 0.7538
10.250 0.4854 0.04304 0.03772 0.0733 0.2412 0.7544
10.500 0.5059 0.04338 0.03806 0.0729 0.2370 0.7550
10.750 0.5251 0.04376 0.03843 0.0725 0.2317 0.7557
11.000 0.5445 0.04413 0.03877 0.0718 0.2249 0.7566
11.250 0.5817 0.04355 0.03815 0.0660 0.2194 0.7598
11.500 0.6026 0.04397 0.03858 0.0656 0.2167 0.7599
11.750 0.6230 0.04441 0.03904 0.0653 0.2134 0.7600
12.000 0.6426 0.04491 0.03954 0.0651 0.2094 0.7601
12.250 0.6601 0.04553 0.04014 0.0651 0.2034 0.7602
12.500 0.6782 0.04615 0.04077 0.0650 0.1978 0.7604
12.750 0.6961 0.04679 0.04139 0.0648 0.1902 0.7605
13.000 0.7120 0.04756 0.04210 0.0649 0.1804 0.7606
13.250 0.7304 0.04819 0.04272 0.0647 0.1724 0.7607
13.500 0.7463 0.04897 0.04344 0.0647 0.1627 0.7609
13.750 0.7611 0.04983 0.04425 0.0647 0.1512 0.7610
14.000 0.7724 0.05093 0.04527 0.0651 0.1358 0.7612
14.250 0.7833 0.05206 0.04630 0.0655 0.1197 0.7613
14.500 0.7953 0.05315 0.04731 0.0658 0.1061 0.7615
14.750 0.8083 0.05420 0.04831 0.0659 0.0961 0.7616
15.000 0.8213 0.05531 0.04940 0.0659 0.0890 0.7618
15.250 0.8350 0.05636 0.05044 0.0658 0.0830 0.7619
15.500 0.8487 0.05743 0.05149 0.0657 0.0772 0.7621
15.750 0.8642 0.05840 0.05245 0.0654 0.0722 0.7623
16.000 0.8780 0.05951 0.05354 0.0652 0.0671 0.7625
16.250 0.8896 0.06083 0.05486 0.0651 0.0614 0.7627
16.500 0.9019 0.06211 0.05613 0.0649 0.0554 0.7628
16.750 0.9134 0.06344 0.05743 0.0647 0.0488 0.7630
17.000 0.9235 0.06490 0.05885 0.0646 0.0420 0.7633
17.250 0.9308 0.06663 0.06058 0.0647 0.0364 0.7635
17.500 0.9399 0.06826 0.06220 0.0645 0.0319 0.7638
17.750 0.9508 0.06979 0.06373 0.0641 0.0286 0.7640
18.000 0.9605 0.07147 0.06542 0.0637 0.0259 0.7642
18.250 0.9698 0.07323 0.06722 0.0631 0.0240 0.7644
18.500 0.9795 0.07496 0.06896 0.0625 0.0222 0.7647
18.750 0.9910 0.07658 0.07061 0.0618 0.0209 0.7649
19.000 0.9989 0.07860 0.07267 0.0610 0.0197 0.7652
19.250 1.0076 0.08057 0.07467 0.0602 0.0185 0.7655
|
Polar data table (+)
Polar graphs
<< Back to Griffith 30% Suction Airfoil (griffith30symsuction-il)