RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.32 at α=10.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5212-il-1000000-n5.txt Download as CSV file: xf-rae5212-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5212 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9183 0.09547 0.09294 -0.0465 1.0000 0.0078
-17.000 -0.9937 0.07630 0.07349 -0.0577 1.0000 0.0077
-16.750 -1.0248 0.06677 0.06377 -0.0636 1.0000 0.0077
-16.500 -1.0490 0.05933 0.05617 -0.0680 1.0000 0.0077
-16.250 -1.0646 0.05395 0.05065 -0.0708 1.0000 0.0078
-16.000 -1.0773 0.04940 0.04597 -0.0728 1.0000 0.0078
-15.750 -1.0849 0.04576 0.04221 -0.0741 1.0000 0.0078
-15.500 -1.0923 0.04238 0.03871 -0.0749 1.0000 0.0078
-15.250 -1.0974 0.03943 0.03565 -0.0754 1.0000 0.0078
-15.000 -1.0992 0.03699 0.03311 -0.0754 1.0000 0.0079
-14.750 -1.0994 0.03485 0.03087 -0.0750 1.0000 0.0079
-14.500 -1.1032 0.03254 0.02847 -0.0744 1.0000 0.0080
-14.250 -1.1066 0.03046 0.02628 -0.0734 1.0000 0.0081
-14.000 -1.1101 0.02858 0.02430 -0.0720 1.0000 0.0082
-13.750 -1.1123 0.02707 0.02272 -0.0701 1.0000 0.0082
-13.500 -1.1172 0.02581 0.02139 -0.0673 1.0000 0.0083
-13.250 -1.1300 0.02486 0.02036 -0.0623 1.0000 0.0084
-13.000 -1.1115 0.02384 0.01927 -0.0625 0.9988 0.0085
-12.750 -1.0872 0.02285 0.01821 -0.0635 0.9972 0.0086
-12.500 -1.0614 0.02198 0.01727 -0.0646 0.9956 0.0088
-12.250 -1.0345 0.02116 0.01638 -0.0658 0.9943 0.0090
-12.000 -1.0103 0.02042 0.01559 -0.0662 0.9924 0.0092
-11.750 -0.9852 0.01975 0.01485 -0.0666 0.9905 0.0095
-11.500 -0.9593 0.01903 0.01407 -0.0673 0.9886 0.0096
-11.250 -0.9323 0.01834 0.01330 -0.0681 0.9871 0.0098
-11.000 -0.9043 0.01768 0.01257 -0.0690 0.9859 0.0100
-10.750 -0.8753 0.01705 0.01187 -0.0700 0.9848 0.0102
-10.500 -0.8460 0.01638 0.01114 -0.0711 0.9839 0.0104
-10.250 -0.8241 0.01575 0.01046 -0.0706 0.9809 0.0106
-10.000 -0.7983 0.01519 0.00987 -0.0708 0.9785 0.0109
-9.750 -0.7697 0.01474 0.00940 -0.0714 0.9767 0.0112
-9.500 -0.7398 0.01427 0.00889 -0.0723 0.9753 0.0115
-9.250 -0.7089 0.01381 0.00840 -0.0734 0.9741 0.0119
-9.000 -0.6781 0.01339 0.00794 -0.0745 0.9729 0.0122
-8.750 -0.6521 0.01299 0.00751 -0.0744 0.9701 0.0125
-8.500 -0.6282 0.01263 0.00711 -0.0739 0.9656 0.0128
-8.250 -0.6002 0.01221 0.00666 -0.0742 0.9624 0.0132
-8.000 -0.5706 0.01181 0.00626 -0.0749 0.9599 0.0138
-7.750 -0.5459 0.01151 0.00594 -0.0744 0.9548 0.0144
-7.500 -0.5189 0.01121 0.00562 -0.0744 0.9500 0.0150
-7.250 -0.4892 0.01089 0.00527 -0.0750 0.9463 0.0156
-7.000 -0.4626 0.01061 0.00496 -0.0749 0.9405 0.0161
-6.750 -0.4349 0.01027 0.00462 -0.0750 0.9338 0.0169
-6.500 -0.4065 0.01000 0.00433 -0.0752 0.9269 0.0178
-6.250 -0.3783 0.00977 0.00406 -0.0754 0.9180 0.0187
-6.000 -0.3502 0.00955 0.00381 -0.0755 0.9094 0.0197
-5.500 -0.2953 0.00911 0.00331 -0.0754 0.8910 0.0222
-5.250 -0.2680 0.00895 0.00310 -0.0753 0.8824 0.0233
-5.000 -0.2414 0.00876 0.00289 -0.0751 0.8733 0.0251
-4.750 -0.2144 0.00861 0.00272 -0.0749 0.8654 0.0270
-4.500 -0.1876 0.00847 0.00255 -0.0747 0.8570 0.0296
-4.250 -0.1608 0.00833 0.00240 -0.0745 0.8493 0.0334
-4.000 -0.1340 0.00818 0.00225 -0.0743 0.8415 0.0386
-3.750 -0.1072 0.00804 0.00211 -0.0740 0.8341 0.0458
-3.500 -0.0803 0.00789 0.00199 -0.0738 0.8266 0.0551
-3.000 -0.0269 0.00754 0.00173 -0.0734 0.8124 0.0928
-2.750 -0.0008 0.00729 0.00160 -0.0732 0.8051 0.1346
-2.500 0.0252 0.00698 0.00147 -0.0729 0.7983 0.1881
-2.250 0.0501 0.00651 0.00129 -0.0726 0.7910 0.2838
-2.000 0.0748 0.00604 0.00114 -0.0722 0.7841 0.3864
-1.750 0.0999 0.00567 0.00105 -0.0718 0.7752 0.4778
-1.500 0.1263 0.00556 0.00106 -0.0715 0.7650 0.5330
-1.250 0.1530 0.00557 0.00106 -0.0711 0.7502 0.5556
-1.000 0.1788 0.00564 0.00107 -0.0705 0.7268 0.5715
-0.750 0.2045 0.00572 0.00108 -0.0699 0.7031 0.5822
-0.500 0.2311 0.00580 0.00108 -0.0695 0.6822 0.5884
-0.250 0.2574 0.00589 0.00109 -0.0691 0.6601 0.5928
0.000 0.2826 0.00604 0.00111 -0.0684 0.6259 0.5961
0.250 0.3055 0.00634 0.00115 -0.0673 0.5633 0.5993
0.500 0.3288 0.00667 0.00123 -0.0664 0.5043 0.6020
0.750 0.3507 0.00710 0.00136 -0.0652 0.4282 0.6049
1.000 0.3738 0.00748 0.00150 -0.0644 0.3663 0.6080
1.250 0.3974 0.00783 0.00163 -0.0636 0.3095 0.6112
1.500 0.4217 0.00814 0.00175 -0.0629 0.2646 0.6143
1.750 0.4465 0.00843 0.00187 -0.0623 0.2267 0.6172
2.000 0.4712 0.00870 0.00200 -0.0617 0.1922 0.6200
2.250 0.4958 0.00897 0.00214 -0.0611 0.1603 0.6229
2.500 0.5209 0.00921 0.00228 -0.0605 0.1348 0.6261
2.750 0.5461 0.00944 0.00242 -0.0600 0.1156 0.6294
3.000 0.5715 0.00966 0.00256 -0.0596 0.1004 0.6325
3.250 0.5970 0.00987 0.00270 -0.0591 0.0875 0.6354
3.500 0.6227 0.01003 0.00284 -0.0586 0.0809 0.6388
3.750 0.6484 0.01021 0.00300 -0.0582 0.0754 0.6422
4.000 0.6744 0.01035 0.00315 -0.0578 0.0732 0.6457
4.250 0.7002 0.01052 0.00330 -0.0574 0.0702 0.6489
4.500 0.7257 0.01071 0.00347 -0.0570 0.0680 0.6516
4.750 0.7510 0.01089 0.00365 -0.0564 0.0657 0.6548
5.000 0.7763 0.01106 0.00384 -0.0559 0.0640 0.6582
5.250 0.8019 0.01122 0.00401 -0.0555 0.0632 0.6616
5.500 0.8273 0.01138 0.00420 -0.0551 0.0621 0.6648
6.000 0.8773 0.01175 0.00460 -0.0540 0.0599 0.6709
6.250 0.9018 0.01195 0.00483 -0.0534 0.0587 0.6743
6.500 0.9261 0.01217 0.00505 -0.0527 0.0574 0.6780
6.750 0.9500 0.01242 0.00531 -0.0520 0.0560 0.6819
7.000 0.9733 0.01270 0.00562 -0.0512 0.0545 0.6856
7.250 0.9972 0.01291 0.00587 -0.0505 0.0540 0.6897
7.500 1.0212 0.01310 0.00610 -0.0498 0.0534 0.6940
7.750 1.0450 0.01331 0.00635 -0.0491 0.0526 0.6982
8.000 1.0683 0.01353 0.00661 -0.0483 0.0517 0.7025
8.250 1.0912 0.01376 0.00688 -0.0475 0.0507 0.7076
8.500 1.1138 0.01401 0.00717 -0.0466 0.0497 0.7131
8.750 1.1359 0.01428 0.00746 -0.0456 0.0487 0.7187
9.000 1.1575 0.01456 0.00777 -0.0446 0.0475 0.7257
9.500 1.1977 0.01514 0.00846 -0.0419 0.0455 0.7428
9.750 1.2176 0.01536 0.00876 -0.0405 0.0448 0.7545
10.000 1.2369 0.01559 0.00907 -0.0391 0.0439 0.7708
10.250 1.2557 0.01582 0.00939 -0.0375 0.0426 0.7948
10.500 1.2715 0.01595 0.00971 -0.0354 0.0413 0.8589
10.750 1.3012 0.01620 0.01016 -0.0363 0.0398 1.0000
11.000 1.3192 0.01660 0.01058 -0.0347 0.0389 1.0000
11.250 1.3376 0.01697 0.01100 -0.0333 0.0383 1.0000
11.500 1.3557 0.01735 0.01142 -0.0318 0.0376 1.0000
11.750 1.3735 0.01776 0.01186 -0.0303 0.0367 1.0000
12.000 1.3909 0.01820 0.01233 -0.0289 0.0358 1.0000
12.250 1.4078 0.01867 0.01282 -0.0274 0.0348 1.0000
12.500 1.4238 0.01919 0.01336 -0.0258 0.0337 1.0000
12.750 1.4396 0.01973 0.01393 -0.0242 0.0328 1.0000
13.000 1.4556 0.02024 0.01450 -0.0227 0.0320 1.0000
13.250 1.4711 0.02080 0.01511 -0.0212 0.0310 1.0000
13.500 1.4858 0.02141 0.01576 -0.0196 0.0300 1.0000
13.750 1.4997 0.02209 0.01647 -0.0180 0.0288 1.0000
14.000 1.5126 0.02285 0.01726 -0.0164 0.0278 1.0000
14.250 1.5262 0.02356 0.01803 -0.0149 0.0266 1.0000
14.500 1.5388 0.02436 0.01888 -0.0134 0.0256 1.0000
14.750 1.5499 0.02528 0.01983 -0.0118 0.0239 1.0000
15.000 1.5605 0.02625 0.02085 -0.0102 0.0229 1.0000
15.250 1.5706 0.02729 0.02194 -0.0088 0.0214 1.0000
15.500 1.5786 0.02851 0.02320 -0.0072 0.0199 1.0000
15.750 1.5865 0.02977 0.02452 -0.0058 0.0188 1.0000
16.000 1.5931 0.03118 0.02598 -0.0044 0.0176 1.0000
16.250 1.5985 0.03271 0.02758 -0.0030 0.0167 1.0000
16.500 1.6029 0.03438 0.02932 -0.0018 0.0159 1.0000
16.750 1.6074 0.03610 0.03112 -0.0007 0.0154 1.0000
17.000 1.6108 0.03796 0.03306 0.0003 0.0149 1.0000
17.250 1.6118 0.04013 0.03531 0.0011 0.0143 1.0000
17.500 1.6121 0.04246 0.03773 0.0018 0.0139 1.0000
17.750 1.6105 0.04508 0.04045 0.0022 0.0135 1.0000
18.000 1.6082 0.04788 0.04335 0.0024 0.0131 1.0000
18.250 1.6057 0.05085 0.04643 0.0024 0.0129 1.0000
18.500 1.6019 0.05412 0.04981 0.0020 0.0127 1.0000
18.750 1.5962 0.05778 0.05358 0.0013 0.0125 1.0000
19.000 1.5880 0.06196 0.05789 0.0002 0.0123 1.0000
19.250 1.5772 0.06677 0.06282 -0.0015 0.0121 1.0000
|
Polar data table (+)
Polar graphs
<< Back to RAE(NPL) 5212 AIRFOIL (rae5212-il)