GOE 530 AIRFOIL (goe530-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 530 AIRFOIL (goe530-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.38 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe530-il-1000000-n5.txt Download as CSV file: xf-goe530-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 530 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
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0249 0.02811 0.02474 -0.1004 0.9723 0.0259
-14.500 -1.0000 0.02617 0.02262 -0.1022 0.9659 0.0260
-14.250 -0.9715 0.02453 0.02084 -0.1043 0.9590 0.0264
-14.000 -0.9397 0.02325 0.01945 -0.1065 0.9516 0.0266
-13.750 -0.9101 0.02215 0.01824 -0.1079 0.9415 0.0269
-13.500 -0.8847 0.02129 0.01726 -0.1082 0.9310 0.0271
-13.250 -0.8621 0.02058 0.01644 -0.1077 0.9202 0.0273
-13.000 -0.8434 0.01991 0.01566 -0.1064 0.9101 0.0275
-12.750 -0.8241 0.01930 0.01493 -0.1050 0.9015 0.0277
-12.500 -0.8052 0.01872 0.01425 -0.1035 0.8936 0.0279
-12.250 -0.7853 0.01819 0.01362 -0.1021 0.8864 0.0281
-12.000 -0.7654 0.01764 0.01298 -0.1007 0.8799 0.0284
-11.750 -0.7450 0.01713 0.01237 -0.0993 0.8726 0.0286
-11.500 -0.7237 0.01669 0.01182 -0.0980 0.8658 0.0289
-11.250 -0.7021 0.01623 0.01127 -0.0968 0.8590 0.0292
-11.000 -0.6803 0.01579 0.01073 -0.0956 0.8520 0.0293
-10.750 -0.6580 0.01538 0.01022 -0.0944 0.8458 0.0295
-10.500 -0.6363 0.01490 0.00967 -0.0932 0.8384 0.0298
-10.250 -0.6142 0.01449 0.00918 -0.0919 0.8307 0.0301
-10.000 -0.5909 0.01413 0.00877 -0.0909 0.8229 0.0304
-9.750 -0.5674 0.01383 0.00840 -0.0899 0.8143 0.0307
-9.500 -0.5435 0.01352 0.00804 -0.0889 0.8068 0.0310
-9.250 -0.5193 0.01324 0.00770 -0.0880 0.7982 0.0313
-9.000 -0.4952 0.01296 0.00734 -0.0870 0.7899 0.0317
-8.750 -0.4711 0.01270 0.00700 -0.0860 0.7789 0.0320
-8.500 -0.4468 0.01245 0.00667 -0.0851 0.7677 0.0324
-8.000 -0.3977 0.01200 0.00605 -0.0833 0.7464 0.0331
-7.750 -0.3732 0.01179 0.00576 -0.0824 0.7371 0.0334
-7.500 -0.3483 0.01154 0.00547 -0.0815 0.7276 0.0340
-7.250 -0.3236 0.01136 0.00522 -0.0807 0.7178 0.0344
-7.000 -0.2979 0.01117 0.00500 -0.0800 0.7089 0.0349
-6.500 -0.2467 0.01085 0.00458 -0.0785 0.6928 0.0359
-6.250 -0.2209 0.01068 0.00437 -0.0778 0.6856 0.0365
-6.000 -0.1951 0.01054 0.00416 -0.0771 0.6793 0.0370
-5.750 -0.1686 0.01038 0.00396 -0.0766 0.6737 0.0374
-5.500 -0.1428 0.01020 0.00377 -0.0759 0.6671 0.0381
-5.250 -0.1169 0.01008 0.00361 -0.0753 0.6604 0.0388
-5.000 -0.0903 0.00996 0.00348 -0.0747 0.6542 0.0396
-4.750 -0.0640 0.00985 0.00335 -0.0741 0.6474 0.0404
-4.500 -0.0379 0.00975 0.00321 -0.0735 0.6415 0.0411
-4.250 -0.0112 0.00965 0.00307 -0.0730 0.6350 0.0418
-4.000 0.0147 0.00953 0.00294 -0.0724 0.6273 0.0427
-3.750 0.0410 0.00945 0.00284 -0.0718 0.6205 0.0436
-3.500 0.0675 0.00936 0.00274 -0.0712 0.6133 0.0445
-3.250 0.0933 0.00931 0.00265 -0.0706 0.6052 0.0454
-3.000 0.1198 0.00924 0.00255 -0.0700 0.5966 0.0463
-2.750 0.1455 0.00920 0.00246 -0.0693 0.5872 0.0472
-2.500 0.1717 0.00913 0.00239 -0.0687 0.5778 0.0485
-2.250 0.1970 0.00912 0.00234 -0.0680 0.5638 0.0495
-2.000 0.2217 0.00913 0.00228 -0.0671 0.5449 0.0506
-1.750 0.2458 0.00918 0.00224 -0.0661 0.5213 0.0516
-1.500 0.2696 0.00926 0.00220 -0.0651 0.4982 0.0524
-1.250 0.2935 0.00930 0.00218 -0.0641 0.4778 0.0538
-1.000 0.3180 0.00935 0.00218 -0.0632 0.4623 0.0551
-0.750 0.3430 0.00939 0.00217 -0.0625 0.4497 0.0565
-0.500 0.3676 0.00944 0.00217 -0.0616 0.4365 0.0577
-0.250 0.3923 0.00948 0.00217 -0.0608 0.4260 0.0589
0.000 0.4173 0.00949 0.00217 -0.0600 0.4170 0.0604
0.250 0.4422 0.00953 0.00218 -0.0592 0.4090 0.0620
0.500 0.4673 0.00955 0.00219 -0.0585 0.4023 0.0634
0.750 0.4926 0.00958 0.00220 -0.0578 0.3952 0.0648
1.000 0.5167 0.00964 0.00223 -0.0569 0.3869 0.0666
1.250 0.5419 0.00965 0.00225 -0.0562 0.3803 0.0685
1.500 0.5665 0.00969 0.00228 -0.0554 0.3736 0.0705
1.750 0.5910 0.00975 0.00231 -0.0546 0.3675 0.0723
2.000 0.6158 0.00977 0.00234 -0.0538 0.3616 0.0749
2.250 0.6398 0.00982 0.00239 -0.0529 0.3546 0.0777
2.500 0.6639 0.00989 0.00244 -0.0521 0.3481 0.0804
2.750 0.6877 0.00995 0.00249 -0.0511 0.3398 0.0846
3.000 0.7106 0.01003 0.00257 -0.0501 0.3318 0.0907
3.250 0.7339 0.01006 0.00264 -0.0490 0.3248 0.1088
3.500 0.7546 0.01004 0.00276 -0.0476 0.3171 0.1844
3.750 0.7753 0.00996 0.00287 -0.0461 0.3103 0.2708
4.000 0.7731 0.00904 0.00301 -0.0400 0.3047 0.7039
4.250 0.8734 0.00911 0.00366 -0.0559 0.2896 0.9698
4.500 0.9193 0.00951 0.00398 -0.0599 0.2776 0.9769
4.750 0.9414 0.00982 0.00421 -0.0587 0.2657 0.9818
5.000 0.9867 0.01019 0.00448 -0.0627 0.2521 0.9841
5.250 1.0253 0.01048 0.00470 -0.0652 0.2418 0.9864
5.500 1.0581 0.01076 0.00493 -0.0664 0.2343 0.9887
5.750 1.0868 0.01097 0.00511 -0.0668 0.2287 0.9905
6.000 1.1109 0.01118 0.00530 -0.0661 0.2238 0.9918
6.250 1.1411 0.01147 0.00553 -0.0669 0.2173 0.9935
6.500 1.1680 0.01163 0.00570 -0.0669 0.2135 0.9941
6.750 1.1942 0.01183 0.00588 -0.0668 0.2092 0.9948
7.000 1.2187 0.01207 0.00609 -0.0664 0.2043 0.9956
7.250 1.2431 0.01228 0.00629 -0.0660 0.2004 0.9964
7.500 1.2673 0.01250 0.00650 -0.0655 0.1956 0.9972
7.750 1.2903 0.01276 0.00674 -0.0649 0.1903 0.9981
8.000 1.3127 0.01301 0.00697 -0.0641 0.1864 0.9989
8.250 1.3355 0.01321 0.00718 -0.0634 0.1829 0.9996
8.500 1.3523 0.01344 0.00741 -0.0615 0.1790 1.0000
8.750 1.3590 0.01373 0.00768 -0.0576 0.1738 1.0000
9.000 1.3688 0.01399 0.00795 -0.0543 0.1698 1.0000
9.250 1.3790 0.01429 0.00825 -0.0512 0.1649 1.0000
9.500 1.3875 0.01470 0.00864 -0.0479 0.1589 1.0000
9.750 1.3982 0.01507 0.00901 -0.0451 0.1527 1.0000
10.000 1.4061 0.01560 0.00949 -0.0420 0.1442 1.0000
10.250 1.4104 0.01633 0.01014 -0.0385 0.1286 1.0000
10.500 1.3952 0.01807 0.01162 -0.0326 0.0901 1.0000
10.750 1.3991 0.01903 0.01255 -0.0295 0.0814 1.0000
11.000 1.4083 0.01977 0.01330 -0.0272 0.0775 1.0000
11.250 1.4174 0.02057 0.01410 -0.0250 0.0745 1.0000
11.500 1.4264 0.02142 0.01496 -0.0229 0.0717 1.0000
11.750 1.4380 0.02216 0.01574 -0.0212 0.0700 1.0000
12.000 1.4487 0.02298 0.01659 -0.0195 0.0683 1.0000
12.250 1.4576 0.02396 0.01759 -0.0177 0.0660 1.0000
12.500 1.4661 0.02499 0.01864 -0.0161 0.0642 1.0000
12.750 1.4760 0.02598 0.01967 -0.0146 0.0628 1.0000
13.000 1.4860 0.02699 0.02072 -0.0132 0.0614 1.0000
13.250 1.4950 0.02811 0.02188 -0.0119 0.0600 1.0000
13.500 1.5035 0.02931 0.02311 -0.0106 0.0589 1.0000
13.750 1.5102 0.03070 0.02453 -0.0093 0.0574 1.0000
14.000 1.5165 0.03215 0.02602 -0.0081 0.0559 1.0000
14.250 1.5250 0.03347 0.02739 -0.0071 0.0551 1.0000
14.500 1.5322 0.03495 0.02892 -0.0061 0.0542 1.0000
14.750 1.5385 0.03656 0.03058 -0.0053 0.0531 1.0000
15.000 1.5440 0.03826 0.03233 -0.0044 0.0521 1.0000
15.250 1.5480 0.04017 0.03428 -0.0037 0.0511 1.0000
15.500 1.5509 0.04223 0.03639 -0.0030 0.0502 1.0000
15.750 1.5533 0.04441 0.03863 -0.0024 0.0493 1.0000
16.000 1.5580 0.04639 0.04068 -0.0020 0.0486 1.0000
16.250 1.5604 0.04865 0.04300 -0.0016 0.0480 1.0000
16.500 1.5619 0.05107 0.04549 -0.0013 0.0472 1.0000
16.750 1.5623 0.05368 0.04816 -0.0012 0.0463 1.0000
17.000 1.5608 0.05654 0.05107 -0.0011 0.0453 1.0000
17.250 1.5580 0.05961 0.05421 -0.0012 0.0445 1.0000
17.500 1.5530 0.06303 0.05770 -0.0014 0.0435 1.0000
17.750 1.5509 0.06617 0.06091 -0.0017 0.0430 1.0000
18.000 1.5478 0.06948 0.06431 -0.0021 0.0423 1.0000
18.250 1.5426 0.07309 0.06800 -0.0026 0.0416 1.0000
18.500 1.5361 0.07695 0.07194 -0.0033 0.0411 1.0000
18.750 1.5282 0.08105 0.07612 -0.0041 0.0404 1.0000
19.000 1.5195 0.08530 0.08046 -0.0050 0.0399 1.0000
19.250 1.5088 0.08984 0.08507 -0.0061 0.0392 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 530 AIRFOIL (goe530-il)