SA7036 (sa7036-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 200,000 Max Cl/Cd: 69.49 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7036-il-200000-n5.txt Download as CSV file: xf-sa7036-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7036
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3963 0.08238 0.07892 -0.0343 1.0000 0.0114
-8.250 -0.3987 0.07910 0.07570 -0.0352 1.0000 0.0111
-8.000 -0.4064 0.07530 0.07198 -0.0361 1.0000 0.0112
-7.750 -0.4172 0.07256 0.06932 -0.0358 1.0000 0.0110
-7.500 -0.4291 0.06923 0.06607 -0.0366 1.0000 0.0109
-7.250 -0.4401 0.06525 0.06213 -0.0380 1.0000 0.0108
-7.000 -0.4372 0.05920 0.05602 -0.0435 0.9972 0.0106
-6.750 -0.4167 0.04929 0.04583 -0.0539 0.9894 0.0105
-6.500 -0.3934 0.04022 0.03628 -0.0612 0.9833 0.0108
-6.250 -0.3711 0.03347 0.02881 -0.0645 0.9761 0.0115
-6.000 -0.3440 0.02837 0.02304 -0.0675 0.9715 0.0122
-5.750 -0.3160 0.02510 0.01924 -0.0688 0.9668 0.0124
-5.500 -0.2869 0.02263 0.01636 -0.0699 0.9618 0.0127
-5.250 -0.2545 0.02065 0.01403 -0.0712 0.9582 0.0133
-5.000 -0.2239 0.01907 0.01217 -0.0719 0.9537 0.0140
-4.750 -0.1947 0.01776 0.01063 -0.0722 0.9478 0.0150
-4.500 -0.1614 0.01694 0.00960 -0.0732 0.9437 0.0170
-4.250 -0.1346 0.01562 0.00819 -0.0731 0.9370 0.0187
-4.000 -0.1046 0.01477 0.00727 -0.0735 0.9311 0.0202
-3.750 -0.0760 0.01410 0.00651 -0.0736 0.9245 0.0220
-3.500 -0.0473 0.01357 0.00589 -0.0737 0.9174 0.0254
-3.250 -0.0193 0.01298 0.00522 -0.0736 0.9101 0.0293
-3.000 0.0092 0.01249 0.00465 -0.0735 0.9023 0.0371
-2.750 0.0360 0.01196 0.00423 -0.0732 0.8932 0.0688
-2.500 0.0636 0.01137 0.00390 -0.0732 0.8851 0.1418
-2.250 0.0891 0.01078 0.00367 -0.0730 0.8747 0.2418
-2.000 0.1144 0.01020 0.00352 -0.0726 0.8645 0.3635
-1.750 0.1396 0.00969 0.00339 -0.0721 0.8545 0.4835
-1.500 0.1648 0.00931 0.00328 -0.0712 0.8440 0.5812
-1.250 0.1888 0.00901 0.00320 -0.0700 0.8318 0.6689
-1.000 0.2122 0.00876 0.00313 -0.0685 0.8190 0.7445
-0.750 0.2355 0.00857 0.00305 -0.0668 0.8056 0.8113
-0.500 0.2618 0.00844 0.00295 -0.0657 0.7914 0.8780
-0.250 0.2982 0.00835 0.00280 -0.0669 0.7765 0.9411
0.000 0.3403 0.00830 0.00262 -0.0696 0.7603 0.9865
0.250 0.3712 0.00834 0.00251 -0.0702 0.7427 1.0000
0.500 0.3964 0.00842 0.00245 -0.0696 0.7247 1.0000
0.750 0.4218 0.00852 0.00241 -0.0689 0.7065 1.0000
1.000 0.4473 0.00863 0.00239 -0.0684 0.6880 1.0000
1.250 0.4729 0.00876 0.00239 -0.0678 0.6685 1.0000
1.500 0.4984 0.00891 0.00241 -0.0672 0.6490 1.0000
1.750 0.5240 0.00906 0.00245 -0.0667 0.6291 1.0000
2.000 0.5496 0.00923 0.00251 -0.0662 0.6090 1.0000
2.250 0.5751 0.00941 0.00259 -0.0657 0.5895 1.0000
2.500 0.6007 0.00960 0.00268 -0.0652 0.5690 1.0000
3.000 0.6514 0.01003 0.00291 -0.0642 0.5266 1.0000
3.250 0.6765 0.01027 0.00307 -0.0637 0.5052 1.0000
3.500 0.7018 0.01050 0.00323 -0.0632 0.4843 1.0000
3.750 0.7268 0.01076 0.00341 -0.0627 0.4640 1.0000
4.000 0.7520 0.01102 0.00363 -0.0622 0.4437 1.0000
4.250 0.7769 0.01130 0.00384 -0.0617 0.4232 1.0000
4.500 0.8017 0.01159 0.00408 -0.0612 0.4031 1.0000
4.750 0.8262 0.01190 0.00433 -0.0607 0.3819 1.0000
5.000 0.8506 0.01224 0.00461 -0.0601 0.3601 1.0000
5.250 0.8747 0.01259 0.00493 -0.0596 0.3385 1.0000
5.500 0.8988 0.01295 0.00525 -0.0590 0.3181 1.0000
5.750 0.9227 0.01332 0.00559 -0.0585 0.2982 1.0000
6.000 0.9464 0.01373 0.00596 -0.0579 0.2794 1.0000
6.250 0.9699 0.01414 0.00637 -0.0573 0.2593 1.0000
6.500 0.9929 0.01460 0.00680 -0.0566 0.2396 1.0000
6.750 1.0158 0.01506 0.00724 -0.0559 0.2193 1.0000
7.000 1.0381 0.01558 0.00772 -0.0552 0.1994 1.0000
7.250 1.0602 0.01611 0.00823 -0.0545 0.1802 1.0000
7.500 1.0819 0.01667 0.00880 -0.0537 0.1614 1.0000
7.750 1.1029 0.01729 0.00938 -0.0528 0.1439 1.0000
8.000 1.1238 0.01791 0.01001 -0.0520 0.1267 1.0000
8.250 1.1441 0.01858 0.01066 -0.0510 0.1096 1.0000
8.500 1.1636 0.01931 0.01138 -0.0500 0.0941 1.0000
8.750 1.1823 0.02009 0.01215 -0.0489 0.0804 1.0000
9.000 1.2006 0.02088 0.01301 -0.0477 0.0690 1.0000
9.250 1.2178 0.02173 0.01389 -0.0464 0.0585 1.0000
9.500 1.2340 0.02264 0.01485 -0.0450 0.0498 1.0000
9.750 1.2477 0.02370 0.01592 -0.0433 0.0428 1.0000
10.000 1.2626 0.02461 0.01692 -0.0417 0.0363 1.0000
10.250 1.2740 0.02562 0.01798 -0.0397 0.0299 1.0000
10.500 1.2833 0.02674 0.01909 -0.0376 0.0242 1.0000
10.750 1.2941 0.02775 0.02022 -0.0356 0.0200 1.0000
11.000 1.3002 0.02913 0.02164 -0.0334 0.0165 1.0000
11.250 1.3071 0.03046 0.02317 -0.0313 0.0144 1.0000
11.500 1.3116 0.03205 0.02487 -0.0292 0.0121 1.0000
11.750 1.3112 0.03409 0.02701 -0.0271 0.0108 1.0000
12.000 1.3122 0.03613 0.02926 -0.0253 0.0093 1.0000
12.250 1.3122 0.03836 0.03165 -0.0239 0.0085 1.0000
12.500 1.3100 0.04094 0.03437 -0.0228 0.0079 1.0000
12.750 1.3061 0.04385 0.03744 -0.0222 0.0076 1.0000
13.000 1.2979 0.04747 0.04122 -0.0220 0.0073 1.0000
13.250 1.2914 0.05115 0.04508 -0.0222 0.0070 1.0000
13.500 1.2854 0.05502 0.04914 -0.0228 0.0067 1.0000
13.750 1.2772 0.05941 0.05373 -0.0240 0.0065 1.0000
14.000 1.2718 0.06365 0.05814 -0.0254 0.0062 1.0000
14.250 1.2616 0.06881 0.06348 -0.0274 0.0061 1.0000
14.500 1.2528 0.07403 0.06887 -0.0297 0.0058 1.0000
14.750 1.2414 0.07993 0.07495 -0.0324 0.0058 1.0000
15.000 1.2291 0.08622 0.08141 -0.0355 0.0058 1.0000
15.250 1.2184 0.09255 0.08789 -0.0388 0.0055 1.0000
15.500 1.2047 0.09957 0.09508 -0.0425 0.0055 1.0000
15.750 1.1919 0.10670 0.10236 -0.0463 0.0055 1.0000
16.000 1.1791 0.11408 0.10989 -0.0504 0.0054 1.0000
16.250 1.1655 0.12178 0.11774 -0.0547 0.0054 1.0000
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