GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 381 AIRFOIL (goe381-il) Reynolds number: 200,000 Max Cl/Cd: 76.41 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe381-il-200000-n5.txt Download as CSV file: xf-goe381-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 381 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2603 0.10017 0.09699 -0.0246 1.0000 0.0151
-7.750 -0.2580 0.09794 0.09483 -0.0246 1.0000 0.0154
-7.500 -0.2535 0.09555 0.09248 -0.0255 0.9964 0.0158
-7.250 -0.2356 0.09195 0.08889 -0.0300 0.9867 0.0164
-7.000 -0.2163 0.08834 0.08528 -0.0349 0.9774 0.0173
-6.750 -0.1933 0.08488 0.08179 -0.0410 0.9681 0.0186
-6.500 -0.1630 0.08206 0.07894 -0.0501 0.9575 0.0195
-6.250 -0.1335 0.07884 0.07568 -0.0584 0.9480 0.0197
-6.000 -0.1061 0.07520 0.07198 -0.0646 0.9397 0.0198
-5.750 -0.0827 0.07153 0.06827 -0.0688 0.9305 0.0198
-5.500 -0.0581 0.06775 0.06443 -0.0729 0.9227 0.0198
-5.250 -0.0343 0.06406 0.06068 -0.0763 0.9138 0.0198
-5.000 -0.0104 0.06033 0.05688 -0.0794 0.9049 0.0198
-4.750 0.0112 0.05634 0.05282 -0.0817 0.8970 0.0196
-4.500 0.0213 0.05235 0.04883 -0.0813 0.8875 0.0179
-4.250 0.0496 0.04875 0.04513 -0.0848 0.8792 0.0168
-4.000 0.0829 0.04542 0.04164 -0.0887 0.8704 0.0184
-3.750 0.1163 0.04197 0.03802 -0.0922 0.8610 0.0188
-3.500 0.1472 0.03859 0.03446 -0.0948 0.8521 0.0186
-3.250 0.1806 0.03517 0.03081 -0.0972 0.8423 0.0188
-3.000 0.2143 0.03182 0.02718 -0.0993 0.8320 0.0209
-2.750 0.2370 0.03089 0.02618 -0.0995 0.8196 0.0240
-2.500 0.2687 0.02817 0.02316 -0.1005 0.8066 0.0245
-2.250 0.3003 0.02578 0.02044 -0.1012 0.7923 0.0268
-2.000 0.3346 0.02349 0.01767 -0.1012 0.7771 0.0300
-1.750 0.3615 0.02128 0.01517 -0.1017 0.7597 0.0318
-1.500 0.3879 0.02061 0.01428 -0.1016 0.7401 0.0363
-1.250 0.4171 0.01893 0.01221 -0.1014 0.7195 0.0374
-1.000 0.4455 0.01751 0.01037 -0.1010 0.6972 0.0382
-0.750 0.4733 0.01668 0.00912 -0.1005 0.6731 0.0404
-0.500 0.5001 0.01558 0.00764 -0.1002 0.6487 0.0399
-0.250 0.5269 0.01476 0.00649 -0.0998 0.6262 0.0395
0.000 0.5535 0.01412 0.00558 -0.0994 0.6072 0.0394
0.250 0.5801 0.01362 0.00487 -0.0990 0.5912 0.0395
0.500 0.6067 0.01325 0.00432 -0.0987 0.5760 0.0399
0.750 0.6331 0.01297 0.00391 -0.0984 0.5616 0.0407
1.000 0.6595 0.01270 0.00354 -0.0982 0.5480 0.0428
1.500 0.7127 0.01259 0.00329 -0.0977 0.5226 0.0479
1.750 0.7392 0.01262 0.00327 -0.0976 0.5095 0.0533
2.000 0.7658 0.01267 0.00331 -0.0974 0.4963 0.0610
2.250 0.7924 0.01273 0.00335 -0.0971 0.4831 0.0713
2.500 0.8189 0.01283 0.00341 -0.0969 0.4697 0.0916
2.750 0.8453 0.01296 0.00350 -0.0967 0.4544 0.1076
3.000 0.8713 0.01309 0.00360 -0.0964 0.4361 0.1245
3.250 0.8970 0.01325 0.00370 -0.0962 0.4149 0.1412
3.500 0.9225 0.01343 0.00383 -0.0958 0.3917 0.1611
4.000 0.9696 0.01269 0.00426 -0.0946 0.3452 1.0000
4.250 0.9942 0.01307 0.00450 -0.0942 0.3237 1.0000
4.500 1.0185 0.01346 0.00481 -0.0938 0.3055 1.0000
4.750 1.0429 0.01386 0.00512 -0.0933 0.2900 1.0000
5.000 1.0675 0.01423 0.00545 -0.0930 0.2780 1.0000
5.250 1.0921 0.01458 0.00579 -0.0926 0.2691 1.0000
5.500 1.1154 0.01506 0.00621 -0.0921 0.2504 1.0000
5.750 1.1374 0.01568 0.00665 -0.0914 0.2221 1.0000
6.000 1.1599 0.01623 0.00709 -0.0909 0.1996 1.0000
6.250 1.1802 0.01704 0.00759 -0.0901 0.1455 1.0000
6.500 1.1977 0.01819 0.00844 -0.0889 0.1103 1.0000
7.000 1.2305 0.02075 0.01064 -0.0861 0.0181 1.0000
7.250 1.2504 0.02156 0.01164 -0.0849 0.0143 1.0000
7.500 1.2701 0.02235 0.01261 -0.0837 0.0134 1.0000
7.750 1.2887 0.02324 0.01371 -0.0824 0.0125 1.0000
8.000 1.3058 0.02423 0.01493 -0.0810 0.0112 1.0000
8.250 1.3207 0.02538 0.01627 -0.0793 0.0100 1.0000
8.500 1.3319 0.02676 0.01785 -0.0773 0.0095 1.0000
8.750 1.3372 0.02839 0.01967 -0.0745 0.0091 1.0000
9.000 1.3355 0.03028 0.02172 -0.0710 0.0088 1.0000
9.250 1.3304 0.03254 0.02410 -0.0677 0.0086 1.0000
9.500 1.3243 0.03511 0.02676 -0.0647 0.0085 1.0000
9.750 1.3251 0.03730 0.02905 -0.0626 0.0084 1.0000
10.000 1.3291 0.03931 0.03118 -0.0609 0.0082 1.0000
10.250 1.3347 0.04123 0.03324 -0.0595 0.0078 1.0000
10.500 1.3391 0.04334 0.03547 -0.0583 0.0073 1.0000
10.750 1.3420 0.04569 0.03799 -0.0571 0.0069 1.0000
11.000 1.3443 0.04821 0.04061 -0.0558 0.0066 1.0000
11.250 1.3473 0.05074 0.04323 -0.0545 0.0065 1.0000
11.500 1.3514 0.05325 0.04584 -0.0532 0.0064 1.0000
11.750 1.3561 0.05578 0.04848 -0.0519 0.0063 1.0000
12.000 1.3612 0.05837 0.05118 -0.0507 0.0062 1.0000
12.250 1.3660 0.06108 0.05402 -0.0495 0.0061 1.0000
12.500 1.3699 0.06397 0.05707 -0.0485 0.0061 1.0000
12.750 1.3719 0.06712 0.06040 -0.0476 0.0061 1.0000
13.000 1.3717 0.07059 0.06406 -0.0471 0.0061 1.0000
13.250 1.3688 0.07440 0.06808 -0.0468 0.0061 1.0000
13.500 1.3633 0.07856 0.07247 -0.0469 0.0062 1.0000
13.750 1.3558 0.08307 0.07720 -0.0475 0.0062 1.0000
14.000 1.3466 0.08791 0.08226 -0.0484 0.0063 1.0000
14.250 1.3360 0.09307 0.08765 -0.0498 0.0064 1.0000
14.500 1.3245 0.09857 0.09335 -0.0517 0.0064 1.0000
14.750 1.3125 0.10438 0.09938 -0.0540 0.0065 1.0000
15.000 1.3002 0.11046 0.10565 -0.0568 0.0066 1.0000
15.250 1.2878 0.11678 0.11215 -0.0600 0.0067 1.0000
15.500 1.2754 0.12340 0.11896 -0.0636 0.0067 1.0000
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Polar data table (+)
Polar graphs
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