GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 417 AIRFOIL (goe417-il) Reynolds number: 200,000 Max Cl/Cd: 78.39 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe417-il-200000-n5.txt Download as CSV file: xf-goe417-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2745 0.10897 0.10560 -0.0250 1.0000 0.0158
-8.500 -0.2764 0.10716 0.10384 -0.0236 1.0000 0.0160
-8.250 -0.2797 0.10549 0.10223 -0.0220 1.0000 0.0161
-8.000 -0.2691 0.10254 0.09929 -0.0241 0.9979 0.0165
-7.750 -0.2521 0.09902 0.09577 -0.0281 0.9941 0.0170
-7.500 -0.2344 0.09564 0.09240 -0.0323 0.9893 0.0184
-7.250 -0.2153 0.09223 0.08899 -0.0371 0.9837 0.0191
-7.000 -0.1889 0.08905 0.08579 -0.0458 0.9767 0.0197
-6.750 -0.1663 0.08569 0.08242 -0.0528 0.9691 0.0198
-6.500 -0.1377 0.08171 0.07841 -0.0605 0.9655 0.0199
-6.250 -0.1158 0.07815 0.07483 -0.0657 0.9585 0.0199
-6.000 -0.0866 0.07397 0.07061 -0.0723 0.9546 0.0199
-5.750 -0.0534 0.06957 0.06617 -0.0794 0.9520 0.0200
-5.500 -0.0304 0.06594 0.06250 -0.0834 0.9444 0.0200
-5.250 -0.0185 0.06195 0.05855 -0.0825 0.9409 0.0206
-5.000 0.0069 0.05915 0.05572 -0.0854 0.9380 0.0232
-4.750 0.0456 0.05620 0.05266 -0.0931 0.9299 0.0258
-4.500 0.0875 0.05237 0.04869 -0.1006 0.9251 0.0261
-4.250 0.1202 0.04882 0.04502 -0.1049 0.9181 0.0262
-4.000 0.1576 0.04511 0.04114 -0.1097 0.9112 0.0264
-3.750 0.1748 0.04126 0.03729 -0.1107 0.9027 0.0275
-3.500 0.2032 0.03869 0.03462 -0.1128 0.8949 0.0290
-3.250 0.2332 0.03615 0.03195 -0.1149 0.8840 0.0313
-3.000 0.2829 0.03393 0.02926 -0.1189 0.8741 0.0355
-2.750 0.3039 0.03019 0.02551 -0.1203 0.8649 0.0379
-2.500 0.3309 0.02832 0.02351 -0.1211 0.8549 0.0403
-2.250 0.3693 0.02601 0.02067 -0.1227 0.8461 0.0482
-1.750 0.4244 0.02185 0.01618 -0.1236 0.8264 0.0437
-1.500 0.4555 0.01927 0.01316 -0.1238 0.8160 0.0387
-1.250 0.4834 0.01829 0.01195 -0.1237 0.8043 0.0417
-1.000 0.5124 0.01685 0.01015 -0.1235 0.7917 0.0402
-0.750 0.5408 0.01562 0.00854 -0.1231 0.7777 0.0388
-0.500 0.5683 0.01478 0.00741 -0.1227 0.7624 0.0384
-0.250 0.5952 0.01414 0.00655 -0.1222 0.7452 0.0386
0.000 0.6217 0.01365 0.00587 -0.1216 0.7252 0.0393
0.250 0.6478 0.01334 0.00541 -0.1210 0.7031 0.0416
0.500 0.6736 0.01301 0.00488 -0.1203 0.6795 0.0419
0.750 0.6991 0.01273 0.00445 -0.1196 0.6572 0.0416
1.000 0.7241 0.01255 0.00412 -0.1188 0.6356 0.0415
1.250 0.7489 0.01244 0.00388 -0.1180 0.6144 0.0415
1.500 0.7734 0.01238 0.00372 -0.1172 0.5927 0.0417
1.750 0.7978 0.01239 0.00362 -0.1165 0.5714 0.0422
2.000 0.8222 0.01243 0.00356 -0.1157 0.5490 0.0430
2.250 0.8461 0.01254 0.00354 -0.1149 0.5246 0.0443
2.750 0.8926 0.01293 0.00360 -0.1130 0.4686 0.0480
3.000 0.9154 0.01316 0.00370 -0.1120 0.4402 0.0557
3.500 0.9657 0.01236 0.00418 -0.1115 0.3930 1.0000
4.000 1.0137 0.01296 0.00457 -0.1100 0.3676 1.0000
4.250 1.0378 0.01325 0.00480 -0.1094 0.3575 1.0000
4.500 1.0615 0.01357 0.00505 -0.1086 0.3483 1.0000
4.750 1.0857 0.01385 0.00532 -0.1080 0.3392 1.0000
5.000 1.1095 0.01416 0.00561 -0.1073 0.3309 1.0000
5.250 1.1333 0.01447 0.00591 -0.1066 0.3225 1.0000
5.500 1.1571 0.01478 0.00622 -0.1060 0.3146 1.0000
5.750 1.1805 0.01511 0.00658 -0.1052 0.3064 1.0000
6.000 1.2041 0.01542 0.00693 -0.1045 0.2983 1.0000
6.250 1.2269 0.01577 0.00730 -0.1037 0.2900 1.0000
6.500 1.2503 0.01608 0.00767 -0.1030 0.2808 1.0000
6.750 1.2727 0.01645 0.00809 -0.1022 0.2702 1.0000
7.000 1.2944 0.01683 0.00848 -0.1012 0.2539 1.0000
7.250 1.3142 0.01732 0.00889 -0.1000 0.2302 1.0000
7.500 1.3333 0.01789 0.00936 -0.0988 0.2032 1.0000
7.750 1.3519 0.01852 0.00994 -0.0975 0.1818 1.0000
8.000 1.3696 0.01923 0.01058 -0.0960 0.1629 1.0000
8.250 1.3866 0.01999 0.01128 -0.0945 0.1445 1.0000
8.500 1.4008 0.02098 0.01213 -0.0927 0.1172 1.0000
8.750 1.4059 0.02274 0.01344 -0.0897 0.0505 1.0000
9.000 1.4093 0.02444 0.01499 -0.0862 0.0231 1.0000
9.250 1.4194 0.02554 0.01620 -0.0836 0.0180 1.0000
9.500 1.4301 0.02658 0.01739 -0.0812 0.0161 1.0000
9.750 1.4387 0.02777 0.01875 -0.0786 0.0147 1.0000
10.000 1.4448 0.02914 0.02030 -0.0758 0.0136 1.0000
10.250 1.4453 0.03093 0.02231 -0.0726 0.0125 1.0000
10.500 1.4482 0.03254 0.02409 -0.0700 0.0118 1.0000
10.750 1.4519 0.03414 0.02586 -0.0677 0.0111 1.0000
11.000 1.4517 0.03614 0.02802 -0.0652 0.0107 1.0000
11.250 1.4500 0.03837 0.03042 -0.0631 0.0103 1.0000
11.500 1.4467 0.04089 0.03313 -0.0611 0.0101 1.0000
11.750 1.4424 0.04369 0.03608 -0.0596 0.0098 1.0000
12.000 1.4372 0.04677 0.03930 -0.0584 0.0095 1.0000
12.250 1.4317 0.05009 0.04277 -0.0576 0.0093 1.0000
12.500 1.4258 0.05367 0.04649 -0.0572 0.0092 1.0000
12.750 1.4197 0.05748 0.05044 -0.0571 0.0090 1.0000
13.000 1.4134 0.06150 0.05459 -0.0573 0.0088 1.0000
13.250 1.4068 0.06571 0.05891 -0.0578 0.0086 1.0000
13.500 1.3995 0.07010 0.06340 -0.0583 0.0084 1.0000
13.750 1.3921 0.07453 0.06791 -0.0585 0.0081 1.0000
14.000 1.3901 0.07848 0.07202 -0.0594 0.0079 1.0000
14.250 1.3877 0.08262 0.07635 -0.0605 0.0076 1.0000
14.500 1.3848 0.08686 0.08074 -0.0615 0.0074 1.0000
14.750 1.3818 0.09119 0.08523 -0.0626 0.0073 1.0000
15.000 1.3786 0.09563 0.08982 -0.0638 0.0071 1.0000
15.250 1.3748 0.10025 0.09464 -0.0652 0.0070 1.0000
15.500 1.3706 0.10504 0.09960 -0.0668 0.0069 1.0000
15.750 1.3657 0.11010 0.10483 -0.0687 0.0068 1.0000
16.000 1.3601 0.11539 0.11030 -0.0709 0.0068 1.0000
16.250 1.3535 0.12100 0.11609 -0.0735 0.0067 1.0000
16.500 1.3463 0.12688 0.12215 -0.0764 0.0066 1.0000
16.750 1.3387 0.13303 0.12848 -0.0797 0.0066 1.0000
17.000 1.3304 0.13947 0.13509 -0.0833 0.0066 1.0000
17.250 1.3215 0.14623 0.14202 -0.0873 0.0066 1.0000
17.500 1.3122 0.15327 0.14924 -0.0916 0.0066 1.0000
17.750 1.3025 0.16064 0.15677 -0.0963 0.0066 1.0000
18.000 1.2923 0.16844 0.16473 -0.1014 0.0066 1.0000
18.250 1.2818 0.17667 0.17312 -0.1068 0.0066 1.0000
18.500 1.2707 0.18547 0.18207 -0.1126 0.0067 1.0000
18.750 1.2592 0.19493 0.19166 -0.1188 0.0068 1.0000
19.000 1.2468 0.20532 0.20217 -0.1255 0.0069 1.0000
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Polar data table (+)
Polar graphs
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