GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.69 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe701-il-1000000.txt Download as CSV file: xf-goe701-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 701 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7422 0.08582 0.08354 -0.0706 1.0000 0.0239
-15.500 -0.7822 0.07746 0.07511 -0.0748 1.0000 0.0240
-15.250 -1.1001 0.03169 0.02856 -0.1068 0.9944 0.0203
-15.000 -1.0911 0.02809 0.02476 -0.1088 0.9912 0.0211
-14.750 -1.0737 0.02599 0.02254 -0.1098 0.9882 0.0218
-14.500 -1.0496 0.02460 0.02105 -0.1110 0.9862 0.0228
-14.250 -1.0225 0.02351 0.01984 -0.1122 0.9847 0.0237
-14.000 -0.9958 0.02220 0.01842 -0.1136 0.9834 0.0247
-13.750 -0.9665 0.02118 0.01735 -0.1151 0.9825 0.0258
-13.500 -0.9457 0.02052 0.01663 -0.1144 0.9788 0.0267
-13.250 -0.9187 0.01989 0.01591 -0.1148 0.9763 0.0277
-13.000 -0.8905 0.01908 0.01501 -0.1156 0.9744 0.0286
-12.750 -0.8604 0.01837 0.01428 -0.1167 0.9730 0.0298
-12.500 -0.8282 0.01787 0.01373 -0.1180 0.9720 0.0308
-12.250 -0.7947 0.01745 0.01325 -0.1194 0.9712 0.0319
-12.000 -0.7598 0.01708 0.01279 -0.1211 0.9705 0.0327
-11.750 -0.7280 0.01624 0.01192 -0.1226 0.9695 0.0341
-11.500 -0.7065 0.01589 0.01154 -0.1214 0.9645 0.0349
-11.250 -0.6760 0.01555 0.01117 -0.1221 0.9618 0.0359
-11.000 -0.6439 0.01522 0.01078 -0.1231 0.9594 0.0369
-10.750 -0.6113 0.01493 0.01042 -0.1241 0.9572 0.0376
-10.500 -0.5822 0.01419 0.00961 -0.1248 0.9542 0.0388
-10.250 -0.5613 0.01382 0.00921 -0.1234 0.9476 0.0397
-10.000 -0.5329 0.01350 0.00886 -0.1236 0.9431 0.0406
-9.750 -0.5011 0.01324 0.00855 -0.1244 0.9394 0.0417
-9.500 -0.4794 0.01299 0.00825 -0.1231 0.9317 0.0425
-9.250 -0.4511 0.01274 0.00791 -0.1231 0.9259 0.0432
-9.000 -0.4266 0.01237 0.00747 -0.1224 0.9187 0.0440
-8.750 -0.4027 0.01185 0.00691 -0.1217 0.9106 0.0455
-8.500 -0.3771 0.01159 0.00661 -0.1212 0.9025 0.0465
-8.250 -0.3507 0.01136 0.00632 -0.1208 0.8938 0.0476
-8.000 -0.3252 0.01114 0.00604 -0.1202 0.8845 0.0486
-7.750 -0.2984 0.01094 0.00575 -0.1198 0.8755 0.0495
-7.500 -0.2729 0.01079 0.00552 -0.1192 0.8656 0.0501
-7.250 -0.2491 0.01034 0.00499 -0.1184 0.8563 0.0515
-7.000 -0.2245 0.01004 0.00464 -0.1176 0.8468 0.0528
-6.750 -0.1990 0.00984 0.00439 -0.1170 0.8382 0.0540
-6.500 -0.1733 0.00969 0.00418 -0.1164 0.8296 0.0554
-6.250 -0.1474 0.00953 0.00396 -0.1159 0.8219 0.0565
-6.000 -0.1214 0.00940 0.00376 -0.1153 0.8139 0.0574
-5.750 -0.0962 0.00917 0.00347 -0.1147 0.8068 0.0591
-5.500 -0.0707 0.00895 0.00324 -0.1140 0.7994 0.0612
-5.250 -0.0448 0.00883 0.00307 -0.1135 0.7926 0.0632
-5.000 -0.0184 0.00870 0.00292 -0.1130 0.7858 0.0652
-4.750 0.0076 0.00858 0.00274 -0.1125 0.7790 0.0672
-4.500 0.0336 0.00842 0.00259 -0.1119 0.7729 0.0711
-4.250 0.0600 0.00833 0.00248 -0.1115 0.7662 0.0746
-4.000 0.0860 0.00823 0.00237 -0.1109 0.7599 0.0800
-3.750 0.1129 0.00816 0.00232 -0.1106 0.7538 0.0854
-3.500 0.1392 0.00808 0.00225 -0.1101 0.7474 0.0917
-3.250 0.1661 0.00808 0.00222 -0.1097 0.7414 0.0966
-3.000 0.1929 0.00802 0.00215 -0.1093 0.7351 0.1002
-2.750 0.2190 0.00796 0.00208 -0.1088 0.7288 0.1049
-2.500 0.2457 0.00793 0.00205 -0.1084 0.7222 0.1086
-2.250 0.2721 0.00793 0.00201 -0.1079 0.7144 0.1110
-2.000 0.2979 0.00788 0.00192 -0.1073 0.7066 0.1140
-1.750 0.3237 0.00780 0.00185 -0.1067 0.6985 0.1181
-1.500 0.3495 0.00778 0.00181 -0.1061 0.6905 0.1214
-1.250 0.3755 0.00775 0.00176 -0.1056 0.6817 0.1241
-1.000 0.4014 0.00776 0.00173 -0.1050 0.6733 0.1262
-0.750 0.4266 0.00771 0.00167 -0.1043 0.6634 0.1313
-0.500 0.4522 0.00768 0.00164 -0.1037 0.6546 0.1356
-0.250 0.4777 0.00768 0.00162 -0.1030 0.6460 0.1403
0.000 0.5033 0.00766 0.00161 -0.1024 0.6374 0.1478
0.250 0.5283 0.00766 0.00161 -0.1017 0.6282 0.1570
0.500 0.5538 0.00763 0.00163 -0.1011 0.6192 0.1717
0.750 0.5783 0.00765 0.00165 -0.1003 0.6100 0.1876
1.000 0.6038 0.00764 0.00167 -0.0997 0.6005 0.2028
1.250 0.6283 0.00766 0.00169 -0.0989 0.5909 0.2165
1.500 0.6525 0.00768 0.00173 -0.0980 0.5798 0.2314
1.750 0.6767 0.00769 0.00176 -0.0972 0.5686 0.2518
2.000 0.6997 0.00768 0.00182 -0.0962 0.5571 0.2915
2.250 0.7212 0.00759 0.00191 -0.0948 0.5457 0.3794
2.500 0.7272 0.00670 0.00203 -0.0904 0.5362 0.7602
2.750 0.8135 0.00671 0.00244 -0.1031 0.5178 0.9811
3.000 0.8608 0.00696 0.00260 -0.1074 0.5009 0.9899
3.250 0.9046 0.00721 0.00275 -0.1109 0.4825 0.9957
3.500 0.9509 0.00745 0.00288 -0.1151 0.4637 0.9995
3.750 0.9743 0.00763 0.00299 -0.1142 0.4471 1.0000
4.000 0.9919 0.00784 0.00311 -0.1121 0.4294 1.0000
4.250 1.0088 0.00806 0.00324 -0.1098 0.4088 1.0000
4.500 1.0239 0.00834 0.00340 -0.1072 0.3848 1.0000
4.750 1.0384 0.00864 0.00358 -0.1045 0.3616 1.0000
5.000 1.0523 0.00896 0.00378 -0.1017 0.3372 1.0000
5.250 1.0648 0.00932 0.00401 -0.0986 0.3121 1.0000
5.500 1.0785 0.00964 0.00423 -0.0958 0.2919 1.0000
5.750 1.0904 0.00999 0.00446 -0.0926 0.2724 1.0000
6.000 1.1023 0.01025 0.00466 -0.0893 0.2594 1.0000
6.250 1.1155 0.01051 0.00487 -0.0864 0.2486 1.0000
6.500 1.1299 0.01078 0.00509 -0.0837 0.2398 1.0000
6.750 1.1465 0.01101 0.00530 -0.0816 0.2327 1.0000
7.000 1.1635 0.01125 0.00553 -0.0795 0.2269 1.0000
7.250 1.1799 0.01154 0.00578 -0.0774 0.2201 1.0000
7.500 1.1986 0.01177 0.00601 -0.0757 0.2150 1.0000
7.750 1.2155 0.01207 0.00629 -0.0737 0.2092 1.0000
8.000 1.2333 0.01236 0.00657 -0.0720 0.2045 1.0000
8.250 1.2526 0.01260 0.00683 -0.0705 0.2000 1.0000
8.500 1.2699 0.01293 0.00714 -0.0688 0.1945 1.0000
8.750 1.2875 0.01326 0.00747 -0.0671 0.1889 1.0000
9.000 1.3064 0.01355 0.00776 -0.0657 0.1840 1.0000
9.250 1.3230 0.01395 0.00814 -0.0640 0.1779 1.0000
9.500 1.3411 0.01429 0.00849 -0.0625 0.1727 1.0000
9.750 1.3573 0.01473 0.00890 -0.0608 0.1641 1.0000
10.000 1.3737 0.01518 0.00933 -0.0592 0.1561 1.0000
10.250 1.3879 0.01575 0.00985 -0.0573 0.1459 1.0000
10.500 1.4008 0.01640 0.01044 -0.0553 0.1345 1.0000
10.750 1.4115 0.01720 0.01116 -0.0531 0.1200 1.0000
11.000 1.4189 0.01821 0.01206 -0.0505 0.1024 1.0000
11.250 1.4253 0.01932 0.01308 -0.0480 0.0877 1.0000
11.500 1.4292 0.02063 0.01428 -0.0453 0.0698 1.0000
11.750 1.4179 0.02301 0.01642 -0.0412 0.0355 1.0000
12.000 1.4243 0.02431 0.01773 -0.0392 0.0304 1.0000
12.250 1.4334 0.02548 0.01893 -0.0375 0.0284 1.0000
12.500 1.4408 0.02680 0.02029 -0.0358 0.0263 1.0000
12.750 1.4518 0.02789 0.02143 -0.0345 0.0254 1.0000
13.000 1.4610 0.02913 0.02272 -0.0331 0.0242 1.0000
13.250 1.4679 0.03060 0.02423 -0.0317 0.0231 1.0000
13.500 1.4728 0.03227 0.02597 -0.0302 0.0221 1.0000
13.750 1.4823 0.03359 0.02734 -0.0292 0.0216 1.0000
14.000 1.4907 0.03504 0.02885 -0.0281 0.0208 1.0000
14.250 1.4980 0.03662 0.03048 -0.0271 0.0201 1.0000
14.500 1.5034 0.03842 0.03233 -0.0261 0.0194 1.0000
14.750 1.5036 0.04076 0.03474 -0.0250 0.0188 1.0000
15.000 1.5055 0.04300 0.03706 -0.0241 0.0183 1.0000
15.250 1.5137 0.04467 0.03878 -0.0235 0.0178 1.0000
15.500 1.5185 0.04671 0.04089 -0.0229 0.0173 1.0000
15.750 1.5220 0.04894 0.04319 -0.0224 0.0169 1.0000
16.000 1.5236 0.05141 0.04573 -0.0219 0.0165 1.0000
16.250 1.5237 0.05411 0.04849 -0.0215 0.0161 1.0000
16.500 1.5213 0.05718 0.05163 -0.0213 0.0157 1.0000
16.750 1.5121 0.06115 0.05571 -0.0213 0.0154 1.0000
17.000 1.5067 0.06476 0.05941 -0.0213 0.0151 1.0000
17.250 1.5070 0.06771 0.06245 -0.0215 0.0148 1.0000
17.500 1.5034 0.07123 0.06606 -0.0218 0.0146 1.0000
17.750 1.5000 0.07478 0.06970 -0.0223 0.0144 1.0000
18.000 1.4940 0.07873 0.07373 -0.0229 0.0142 1.0000
18.250 1.4877 0.08275 0.07785 -0.0236 0.0139 1.0000
18.500 1.4813 0.08689 0.08207 -0.0244 0.0136 1.0000
18.750 1.4714 0.09159 0.08686 -0.0255 0.0134 1.0000
19.000 1.4614 0.09636 0.09172 -0.0268 0.0132 1.0000
19.250 1.4453 0.10212 0.09760 -0.0284 0.0131 1.0000
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