GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.1 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe117-il-1000000.txt Download as CSV file: xf-goe117-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 117 (MVA MK.4) 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3527 0.10616 0.10453 -0.0367 1.0000 0.0110
-10.000 -0.3600 0.10094 0.09935 -0.0377 1.0000 0.0114
-9.000 -0.4940 0.02200 0.01925 -0.1047 0.9632 0.0085
-8.750 -0.4593 0.02093 0.01803 -0.1074 0.9574 0.0089
-8.500 -0.4295 0.01865 0.01541 -0.1097 0.9468 0.0093
-8.250 -0.3987 0.01720 0.01371 -0.1114 0.9350 0.0098
-8.000 -0.3712 0.01595 0.01218 -0.1122 0.9216 0.0104
-7.750 -0.3444 0.01539 0.01145 -0.1123 0.9095 0.0108
-7.500 -0.3240 0.01353 0.00921 -0.1116 0.8979 0.0117
-7.250 -0.2980 0.01326 0.00886 -0.1115 0.8885 0.0124
-7.000 -0.2719 0.01304 0.00857 -0.1112 0.8801 0.0130
-6.750 -0.2461 0.01270 0.00811 -0.1109 0.8721 0.0138
-6.500 -0.2204 0.01230 0.00759 -0.1106 0.8640 0.0146
-6.250 -0.1940 0.01211 0.00730 -0.1103 0.8563 0.0152
-6.000 -0.1707 0.01106 0.00609 -0.1097 0.8480 0.0167
-5.750 -0.1437 0.01106 0.00606 -0.1096 0.8401 0.0177
-5.500 -0.1169 0.01100 0.00595 -0.1094 0.8319 0.0190
-5.250 -0.0902 0.01082 0.00570 -0.1091 0.8238 0.0203
-4.750 -0.0396 0.00970 0.00435 -0.1083 0.8058 0.0232
-4.500 -0.0133 0.00949 0.00410 -0.1080 0.7958 0.0249
-4.250 0.0129 0.00928 0.00382 -0.1077 0.7842 0.0265
-4.000 0.0390 0.00905 0.00351 -0.1073 0.7701 0.0278
-3.750 0.0650 0.00886 0.00322 -0.1069 0.7525 0.0289
-3.500 0.0909 0.00885 0.00310 -0.1064 0.7297 0.0297
-3.250 0.1151 0.00845 0.00251 -0.1057 0.7001 0.0312
-3.000 0.1396 0.00823 0.00209 -0.1050 0.6704 0.0332
-2.750 0.1649 0.00814 0.00187 -0.1044 0.6480 0.0352
-2.500 0.1909 0.00807 0.00169 -0.1040 0.6318 0.0364
-2.250 0.2173 0.00801 0.00154 -0.1037 0.6193 0.0376
-2.000 0.2440 0.00795 0.00140 -0.1035 0.6095 0.0390
-1.750 0.2707 0.00791 0.00129 -0.1032 0.6012 0.0407
-1.500 0.2976 0.00776 0.00117 -0.1030 0.5941 0.0576
-1.250 0.3231 0.00749 0.00113 -0.1028 0.5875 0.1488
-1.000 0.3504 0.00744 0.00110 -0.1027 0.5817 0.1634
-0.750 0.3773 0.00741 0.00109 -0.1025 0.5762 0.1782
-0.500 0.4042 0.00737 0.00109 -0.1024 0.5714 0.1973
-0.250 0.4313 0.00729 0.00112 -0.1023 0.5666 0.2359
0.000 0.4583 0.00729 0.00115 -0.1021 0.5618 0.2617
0.250 0.4853 0.00731 0.00119 -0.1020 0.5571 0.2780
0.500 0.5127 0.00730 0.00121 -0.1019 0.5520 0.2942
0.750 0.5396 0.00731 0.00125 -0.1018 0.5472 0.3118
1.000 0.5666 0.00732 0.00129 -0.1017 0.5431 0.3280
1.250 0.5940 0.00730 0.00133 -0.1016 0.5395 0.3423
1.500 0.6209 0.00727 0.00137 -0.1015 0.5357 0.3676
1.750 0.6467 0.00713 0.00147 -0.1012 0.5321 0.4634
2.000 0.6912 0.00604 0.00165 -0.1052 0.5275 0.9977
2.250 0.7194 0.00610 0.00169 -0.1054 0.5209 1.0000
2.500 0.7449 0.00620 0.00176 -0.1049 0.5166 1.0000
2.750 0.7711 0.00625 0.00182 -0.1045 0.5087 1.0000
3.000 0.7964 0.00636 0.00189 -0.1040 0.5010 1.0000
3.250 0.8226 0.00642 0.00195 -0.1037 0.4913 1.0000
3.500 0.8481 0.00652 0.00202 -0.1033 0.4780 1.0000
3.750 0.8731 0.00666 0.00211 -0.1027 0.4607 1.0000
4.000 0.8974 0.00685 0.00221 -0.1021 0.4330 1.0000
4.250 0.9165 0.00745 0.00246 -0.1005 0.3606 1.0000
4.500 0.9228 0.00916 0.00330 -0.0970 0.1900 1.0000
4.750 0.9329 0.01060 0.00414 -0.0941 0.0498 1.0000
5.000 0.9556 0.01098 0.00447 -0.0932 0.0354 1.0000
5.250 0.9782 0.01136 0.00482 -0.0923 0.0272 1.0000
5.500 1.0012 0.01168 0.00513 -0.0915 0.0229 1.0000
5.750 1.0226 0.01214 0.00563 -0.0903 0.0192 1.0000
6.000 1.0454 0.01246 0.00598 -0.0895 0.0174 1.0000
6.250 1.0674 0.01283 0.00635 -0.0885 0.0155 1.0000
6.500 1.0840 0.01360 0.00721 -0.0865 0.0137 1.0000
6.750 1.1052 0.01399 0.00762 -0.0854 0.0131 1.0000
7.000 1.1250 0.01444 0.00813 -0.0841 0.0123 1.0000
7.250 1.1439 0.01493 0.00866 -0.0826 0.0115 1.0000
7.500 1.1612 0.01549 0.00926 -0.0809 0.0110 1.0000
7.750 1.1765 0.01613 0.00994 -0.0789 0.0103 1.0000
8.000 1.1779 0.01739 0.01130 -0.0743 0.0097 1.0000
8.250 1.1869 0.01812 0.01211 -0.0712 0.0092 1.0000
8.500 1.1982 0.01879 0.01284 -0.0685 0.0090 1.0000
8.750 1.2092 0.01951 0.01361 -0.0659 0.0086 1.0000
9.000 1.2184 0.02040 0.01458 -0.0632 0.0083 1.0000
9.250 1.2280 0.02131 0.01555 -0.0607 0.0080 1.0000
9.500 1.2372 0.02232 0.01664 -0.0583 0.0078 1.0000
9.750 1.2465 0.02340 0.01778 -0.0560 0.0075 1.0000
10.000 1.2580 0.02429 0.01872 -0.0542 0.0072 1.0000
10.250 1.2669 0.02557 0.02008 -0.0521 0.0072 1.0000
10.500 1.2766 0.02677 0.02133 -0.0503 0.0069 1.0000
10.750 1.2838 0.02851 0.02316 -0.0483 0.0066 1.0000
11.000 1.2958 0.03246 0.02742 -0.0464 0.0063 1.0000
11.250 1.3047 0.03340 0.02847 -0.0447 0.0062 1.0000
11.500 1.3142 0.03489 0.03011 -0.0431 0.0060 1.0000
11.750 1.3226 0.03678 0.03215 -0.0416 0.0058 1.0000
12.000 1.3283 0.03950 0.03511 -0.0398 0.0057 1.0000
12.250 1.3301 0.04261 0.03847 -0.0379 0.0054 1.0000
12.500 1.3301 0.04529 0.04133 -0.0363 0.0053 1.0000
13.000 1.2661 0.06302 0.06005 -0.0313 0.0056 1.0000
13.250 1.2394 0.06933 0.06659 -0.0309 0.0057 1.0000
13.500 1.2141 0.07547 0.07292 -0.0315 0.0058 1.0000
13.750 1.1932 0.08161 0.07923 -0.0328 0.0058 1.0000
14.000 1.1659 0.08868 0.08646 -0.0353 0.0059 1.0000
14.250 1.1428 0.09584 0.09376 -0.0384 0.0060 1.0000
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Polar data table (+)
Polar graphs
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