GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 100,000 Max Cl/Cd: 54.75 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe701-il-100000.txt Download as CSV file: xf-goe701-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3815 0.10571 0.10124 -0.0199 1.0000 0.1363
-7.750 -0.4049 0.10493 0.10054 -0.0184 1.0000 0.1390
-7.500 -0.4462 0.10378 0.09945 -0.0294 0.9911 0.1414
-7.250 -0.4204 0.09838 0.09405 -0.0271 0.9883 0.1433
-7.000 -0.3878 0.09491 0.09054 -0.0267 0.9849 0.1469
-6.750 -0.3768 0.09187 0.08747 -0.0307 0.9774 0.1530
-6.500 -0.3784 0.08656 0.08209 -0.0425 0.9661 0.1589
-6.250 -0.3566 0.08393 0.07948 -0.0401 0.9612 0.1618
-6.000 -0.3544 0.08034 0.07555 -0.0542 0.9476 0.1739
-5.750 -0.3321 0.07602 0.07136 -0.0517 0.9437 0.1755
-5.500 -0.3032 0.07346 0.06883 -0.0512 0.9402 0.1800
-5.250 -0.2991 0.06993 0.06504 -0.0577 0.9287 0.1917
-5.000 -0.2714 0.06686 0.06203 -0.0575 0.9249 0.1947
-4.750 -0.2608 0.06486 0.06000 -0.0567 0.9163 0.1998
-4.500 -0.2363 0.06133 0.05630 -0.0612 0.9100 0.2113
-4.250 -0.2194 0.04594 0.03927 -0.0712 0.9024 0.1424
-4.000 -0.1936 0.04459 0.03802 -0.0717 0.8961 0.1451
-3.750 -0.1570 0.04181 0.03488 -0.0744 0.8922 0.1467
-3.500 -0.1452 0.03980 0.03254 -0.0726 0.8831 0.1466
-3.250 -0.1116 0.03771 0.03008 -0.0741 0.8782 0.1488
-3.000 -0.0866 0.03639 0.02841 -0.0740 0.8716 0.1535
-2.750 -0.0608 0.03502 0.02648 -0.0737 0.8645 0.1578
-2.500 -0.0215 0.03385 0.02536 -0.0760 0.8606 0.1634
-2.250 -0.0060 0.03357 0.02491 -0.0741 0.8513 0.1698
-2.000 0.0298 0.03258 0.02368 -0.0754 0.8461 0.1778
-1.750 0.0598 0.03214 0.02314 -0.0758 0.8401 0.1862
-1.500 0.0830 0.03174 0.02262 -0.0751 0.8318 0.1947
-1.250 0.1258 0.03113 0.02181 -0.0773 0.8279 0.2070
-1.000 0.1388 0.03110 0.02187 -0.0751 0.8179 0.2141
-0.750 0.1780 0.03052 0.02118 -0.0768 0.8130 0.2265
-0.500 0.2032 0.03040 0.02109 -0.0764 0.8056 0.2370
-0.250 0.2320 0.03007 0.02080 -0.0765 0.7982 0.2480
0.000 0.2776 0.02928 0.02001 -0.0790 0.7947 0.2622
0.250 0.2889 0.02965 0.02042 -0.0764 0.7837 0.2714
0.500 0.3320 0.02888 0.01974 -0.0785 0.7795 0.2898
0.750 0.3661 0.02846 0.01942 -0.0792 0.7735 0.3102
1.000 0.3917 0.02826 0.01942 -0.0787 0.7647 0.3369
1.250 0.4457 0.02671 0.01842 -0.0824 0.7622 0.4368
1.500 0.6045 0.02322 0.01595 -0.1045 0.7624 1.0000
1.750 0.6297 0.02300 0.01561 -0.1032 0.7509 1.0000
2.000 0.6840 0.02192 0.01440 -0.1065 0.7452 1.0000
2.250 0.6998 0.02218 0.01460 -0.1040 0.7340 1.0000
2.500 0.7465 0.02147 0.01380 -0.1063 0.7281 1.0000
2.750 0.7613 0.02175 0.01405 -0.1037 0.7165 1.0000
3.000 0.8095 0.02100 0.01321 -0.1063 0.7103 1.0000
3.250 0.8222 0.02131 0.01351 -0.1032 0.6979 1.0000
3.500 0.8510 0.02116 0.01332 -0.1027 0.6881 1.0000
3.750 0.8854 0.02080 0.01290 -0.1031 0.6784 1.0000
4.000 0.9042 0.02088 0.01298 -0.1010 0.6657 1.0000
4.250 0.9314 0.02072 0.01279 -0.1002 0.6540 1.0000
4.500 0.9696 0.02028 0.01226 -0.1012 0.6433 1.0000
4.750 0.9878 0.02034 0.01232 -0.0989 0.6289 1.0000
5.000 1.0089 0.02032 0.01228 -0.0971 0.6140 1.0000
5.250 1.0315 0.02026 0.01219 -0.0955 0.5983 1.0000
5.500 1.0543 0.02021 0.01209 -0.0940 0.5816 1.0000
5.750 1.0771 0.02020 0.01201 -0.0924 0.5637 1.0000
6.000 1.1004 0.02022 0.01192 -0.0910 0.5445 1.0000
6.250 1.1137 0.02048 0.01215 -0.0880 0.5227 1.0000
6.500 1.1310 0.02072 0.01228 -0.0856 0.5004 1.0000
6.750 1.1513 0.02103 0.01240 -0.0839 0.4788 1.0000
7.000 1.1638 0.02153 0.01285 -0.0810 0.4570 1.0000
7.250 1.1795 0.02206 0.01326 -0.0786 0.4368 1.0000
7.500 1.1964 0.02263 0.01372 -0.0766 0.4189 1.0000
7.750 1.2136 0.02325 0.01425 -0.0747 0.4030 1.0000
8.000 1.2308 0.02391 0.01485 -0.0729 0.3884 1.0000
8.250 1.2491 0.02459 0.01546 -0.0713 0.3754 1.0000
8.500 1.2707 0.02528 0.01604 -0.0703 0.3635 1.0000
8.750 1.2866 0.02598 0.01676 -0.0684 0.3522 1.0000
9.000 1.3043 0.02677 0.01759 -0.0669 0.3422 1.0000
9.250 1.3312 0.02755 0.01823 -0.0669 0.3325 1.0000
9.500 1.3412 0.02834 0.01919 -0.0641 0.3235 1.0000
9.750 1.3634 0.02915 0.01994 -0.0634 0.3143 1.0000
10.000 1.3746 0.02989 0.02076 -0.0609 0.3052 1.0000
10.250 1.3886 0.03068 0.02156 -0.0589 0.2962 1.0000
10.500 1.4029 0.03138 0.02226 -0.0569 0.2873 1.0000
10.750 1.4123 0.03226 0.02324 -0.0542 0.2796 1.0000
11.000 1.4268 0.03300 0.02398 -0.0524 0.2715 1.0000
11.250 1.4367 0.03393 0.02501 -0.0499 0.2644 1.0000
11.500 1.4445 0.03470 0.02585 -0.0472 0.2569 1.0000
11.750 1.4574 0.03561 0.02678 -0.0453 0.2497 1.0000
12.000 1.4592 0.03656 0.02791 -0.0419 0.2433 1.0000
12.250 1.4793 0.03731 0.02858 -0.0412 0.2359 1.0000
12.500 1.4714 0.03847 0.03001 -0.0368 0.2302 1.0000
12.750 1.4824 0.03917 0.03069 -0.0349 0.2232 1.0000
13.000 1.4825 0.04040 0.03208 -0.0320 0.2175 1.0000
13.250 1.4802 0.04162 0.03348 -0.0290 0.2117 1.0000
13.500 1.4921 0.04234 0.03414 -0.0275 0.2049 1.0000
13.750 1.4782 0.04415 0.03626 -0.0238 0.1996 1.0000
14.000 1.4765 0.04531 0.03747 -0.0215 0.1928 1.0000
14.250 1.4682 0.04714 0.03947 -0.0190 0.1867 1.0000
14.500 1.4583 0.04913 0.04163 -0.0167 0.1799 1.0000
14.750 1.4506 0.05115 0.04374 -0.0150 0.1731 1.0000
15.000 1.4370 0.05394 0.04675 -0.0134 0.1657 1.0000
15.250 1.4245 0.05688 0.04981 -0.0123 0.1577 1.0000
15.500 1.4104 0.06030 0.05335 -0.0117 0.1489 1.0000
15.750 1.3938 0.06454 0.05778 -0.0116 0.1388 1.0000
16.000 1.3754 0.06932 0.06264 -0.0121 0.1275 1.0000
16.250 1.3562 0.07461 0.06794 -0.0129 0.1166 1.0000
16.500 1.3369 0.08022 0.07352 -0.0141 0.1070 1.0000
16.750 1.3174 0.08616 0.07946 -0.0156 0.0984 1.0000
17.000 1.3000 0.09204 0.08539 -0.0172 0.0910 1.0000
17.250 1.2857 0.09745 0.09069 -0.0187 0.0853 1.0000
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