GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.75 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe137-il-1000000.txt Download as CSV file: xf-goe137-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 137 (MVA H.15) 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4540 0.14673 0.14508 0.0055 1.0000 0.0090
-12.000 -0.4475 0.14316 0.14151 0.0041 1.0000 0.0096
-7.000 -0.3381 0.01711 0.01363 -0.0825 0.9609 0.0145
-6.750 -0.3116 0.01753 0.01410 -0.0819 0.9517 0.0148
-6.500 -0.2859 0.01806 0.01466 -0.0812 0.9414 0.0151
-6.250 -0.2610 0.01761 0.01411 -0.0807 0.9292 0.0157
-6.000 -0.2368 0.01612 0.01231 -0.0802 0.9160 0.0168
-5.750 -0.2112 0.01550 0.01148 -0.0796 0.9011 0.0177
-5.500 -0.1868 0.01414 0.00984 -0.0793 0.8838 0.0188
-5.250 -0.1602 0.01428 0.00994 -0.0790 0.8628 0.0194
-5.000 -0.1339 0.01417 0.00971 -0.0786 0.8379 0.0201
-4.750 -0.1073 0.01380 0.00914 -0.0782 0.8099 0.0211
-4.500 -0.0804 0.01339 0.00849 -0.0780 0.7823 0.0222
-4.250 -0.0526 0.01361 0.00856 -0.0778 0.7581 0.0230
-4.000 -0.0263 0.01192 0.00657 -0.0777 0.7392 0.0247
-3.750 0.0013 0.01164 0.00619 -0.0777 0.7233 0.0256
-3.500 0.0292 0.01137 0.00581 -0.0777 0.7094 0.0266
-3.250 0.0573 0.01110 0.00545 -0.0777 0.6971 0.0278
-3.000 0.0854 0.01073 0.00497 -0.0777 0.6851 0.0287
-2.750 0.1135 0.01042 0.00455 -0.0776 0.6737 0.0295
-2.500 0.1417 0.01023 0.00427 -0.0776 0.6625 0.0301
-2.250 0.1699 0.00982 0.00377 -0.0776 0.6522 0.0311
-2.000 0.1977 0.00916 0.00302 -0.0776 0.6429 0.0319
-1.500 0.2541 0.00852 0.00228 -0.0776 0.6254 0.0334
-1.250 0.2824 0.00834 0.00204 -0.0776 0.6169 0.0345
-1.000 0.3109 0.00820 0.00187 -0.0777 0.6071 0.0359
-0.750 0.3393 0.00808 0.00170 -0.0777 0.5979 0.0371
-0.250 0.3963 0.00791 0.00145 -0.0778 0.5806 0.0394
0.000 0.4247 0.00787 0.00136 -0.0779 0.5718 0.0402
0.250 0.4532 0.00782 0.00126 -0.0779 0.5618 0.0422
0.500 0.4817 0.00776 0.00118 -0.0780 0.5514 0.0504
0.750 0.5099 0.00755 0.00120 -0.0782 0.5405 0.1451
1.000 0.5380 0.00743 0.00123 -0.0783 0.5289 0.2159
1.250 0.5634 0.00625 0.00136 -0.0785 0.5165 0.7340
2.250 0.6745 0.00613 0.00151 -0.0781 0.4585 1.0000
2.500 0.7023 0.00627 0.00158 -0.0781 0.4445 1.0000
2.750 0.7302 0.00641 0.00165 -0.0782 0.4316 1.0000
3.000 0.7580 0.00655 0.00174 -0.0782 0.4195 1.0000
3.250 0.7856 0.00672 0.00183 -0.0782 0.4047 1.0000
3.500 0.8131 0.00689 0.00193 -0.0782 0.3899 1.0000
3.750 0.8407 0.00705 0.00205 -0.0782 0.3777 1.0000
4.000 0.8682 0.00723 0.00217 -0.0782 0.3643 1.0000
4.250 0.8955 0.00742 0.00230 -0.0781 0.3494 1.0000
4.500 0.9225 0.00764 0.00244 -0.0781 0.3321 1.0000
4.750 0.9493 0.00790 0.00261 -0.0780 0.3130 1.0000
5.000 0.9759 0.00817 0.00279 -0.0779 0.2897 1.0000
5.250 1.0018 0.00853 0.00301 -0.0778 0.2597 1.0000
5.500 1.0259 0.00915 0.00337 -0.0774 0.2076 1.0000
5.750 1.0503 0.00969 0.00373 -0.0771 0.1777 1.0000
6.000 1.0759 0.01006 0.00403 -0.0768 0.1638 1.0000
6.250 1.1019 0.01035 0.00429 -0.0767 0.1538 1.0000
6.500 1.1276 0.01067 0.00457 -0.0765 0.1411 1.0000
6.750 1.1481 0.01166 0.00516 -0.0757 0.0769 1.0000
7.000 1.1655 0.01304 0.00617 -0.0743 0.0180 1.0000
7.250 1.1901 0.01344 0.00662 -0.0739 0.0154 1.0000
7.500 1.2139 0.01392 0.00715 -0.0734 0.0138 1.0000
7.750 1.2365 0.01456 0.00786 -0.0726 0.0123 1.0000
8.000 1.2598 0.01505 0.00840 -0.0720 0.0117 1.0000
8.250 1.2829 0.01553 0.00893 -0.0714 0.0111 1.0000
8.500 1.3052 0.01608 0.00952 -0.0707 0.0103 1.0000
8.750 1.3264 0.01671 0.01021 -0.0699 0.0098 1.0000
9.000 1.3453 0.01756 0.01113 -0.0687 0.0092 1.0000
9.250 1.3565 0.01908 0.01279 -0.0664 0.0086 1.0000
9.500 1.3766 0.01965 0.01342 -0.0654 0.0084 1.0000
9.750 1.3945 0.02038 0.01421 -0.0642 0.0082 1.0000
10.000 1.4104 0.02122 0.01513 -0.0626 0.0079 1.0000
10.250 1.4240 0.02215 0.01613 -0.0608 0.0077 1.0000
10.500 1.4347 0.02306 0.01711 -0.0585 0.0074 1.0000
10.750 1.4443 0.02399 0.01810 -0.0562 0.0071 1.0000
11.000 1.4529 0.02503 0.01921 -0.0540 0.0068 1.0000
11.250 1.4607 0.02622 0.02045 -0.0520 0.0066 1.0000
11.500 1.4638 0.02784 0.02215 -0.0498 0.0064 1.0000
11.750 1.4612 0.03010 0.02451 -0.0475 0.0062 1.0000
12.000 1.4518 0.03323 0.02775 -0.0453 0.0061 1.0000
12.250 1.4431 0.03657 0.03121 -0.0434 0.0060 1.0000
12.500 1.4497 0.03851 0.03324 -0.0429 0.0059 1.0000
12.750 1.4540 0.04078 0.03562 -0.0424 0.0058 1.0000
13.000 1.4569 0.04325 0.03819 -0.0420 0.0057 1.0000
13.250 1.4582 0.04597 0.04100 -0.0417 0.0057 1.0000
13.500 1.4580 0.04889 0.04403 -0.0414 0.0056 1.0000
13.750 1.4572 0.05192 0.04717 -0.0413 0.0055 1.0000
14.000 1.4553 0.05513 0.05049 -0.0412 0.0054 1.0000
14.250 1.4524 0.05850 0.05397 -0.0412 0.0054 1.0000
14.500 1.4490 0.06200 0.05758 -0.0413 0.0053 1.0000
14.750 1.4449 0.06570 0.06140 -0.0417 0.0052 1.0000
15.000 1.4399 0.06960 0.06542 -0.0422 0.0052 1.0000
15.250 1.4345 0.07368 0.06961 -0.0429 0.0051 1.0000
15.500 1.4280 0.07802 0.07407 -0.0438 0.0050 1.0000
15.750 1.4213 0.08255 0.07872 -0.0450 0.0050 1.0000
16.000 1.4133 0.08735 0.08365 -0.0463 0.0049 1.0000
16.250 1.4054 0.09229 0.08871 -0.0480 0.0049 1.0000
16.500 1.3960 0.09761 0.09415 -0.0498 0.0048 1.0000
16.750 1.3865 0.10309 0.09976 -0.0519 0.0048 1.0000
17.000 1.3761 0.10880 0.10560 -0.0542 0.0048 1.0000
17.250 1.3657 0.11469 0.11161 -0.0568 0.0047 1.0000
17.500 1.3531 0.12112 0.11818 -0.0598 0.0047 1.0000
17.750 1.3402 0.12782 0.12502 -0.0630 0.0047 1.0000
18.000 1.3287 0.13438 0.13169 -0.0665 0.0047 1.0000
18.250 1.3140 0.14183 0.13928 -0.0705 0.0047 1.0000
18.500 1.2996 0.14952 0.14711 -0.0748 0.0047 1.0000
18.750 1.2865 0.15724 0.15496 -0.0795 0.0047 1.0000
19.000 1.2706 0.16603 0.16390 -0.0849 0.0047 1.0000
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Polar data table (+)
Polar graphs
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