GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.2 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe142-il-1000000.txt Download as CSV file: xf-goe142-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 142 (MVA H.19) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4305 0.11116 0.10953 -0.0019 1.0000 0.0076
-9.000 -0.4244 0.10770 0.10608 -0.0035 1.0000 0.0076
-8.750 -0.4227 0.10316 0.10156 -0.0043 1.0000 0.0078
-8.500 -0.4158 0.10021 0.09861 -0.0054 1.0000 0.0079
-8.250 -0.4089 0.09724 0.09566 -0.0068 1.0000 0.0081
-8.000 -0.4021 0.09427 0.09270 -0.0083 1.0000 0.0082
-7.750 -0.3954 0.09131 0.08976 -0.0098 1.0000 0.0084
-7.500 -0.3893 0.08834 0.08681 -0.0115 1.0000 0.0086
-7.250 -0.3830 0.08529 0.08378 -0.0135 1.0000 0.0089
-7.000 -0.3727 0.08184 0.08034 -0.0168 1.0000 0.0093
-6.750 -0.3617 0.07809 0.07660 -0.0206 1.0000 0.0103
-6.500 -0.3511 0.07430 0.07283 -0.0254 1.0000 0.0109
-6.250 -0.3306 0.06976 0.06827 -0.0312 0.9983 0.0109
-6.000 -0.2968 0.06409 0.06255 -0.0400 0.9955 0.0110
-5.750 -0.2658 0.05612 0.05452 -0.0501 0.9915 0.0114
-5.500 -0.2356 0.05292 0.05126 -0.0548 0.9882 0.0118
-5.250 -0.2032 0.04982 0.04811 -0.0597 0.9846 0.0124
-5.000 -0.1706 0.04600 0.04422 -0.0646 0.9777 0.0135
-4.750 -0.1292 0.04141 0.03947 -0.0701 0.9710 0.0153
-4.500 -0.0907 0.01322 0.00941 -0.0805 0.9603 0.0118
-4.250 -0.0641 0.01214 0.00811 -0.0803 0.9513 0.0123
-4.000 -0.0380 0.01128 0.00705 -0.0798 0.9413 0.0128
-3.750 -0.0119 0.01086 0.00653 -0.0792 0.9299 0.0136
-3.500 0.0146 0.01025 0.00577 -0.0787 0.9184 0.0146
-3.250 0.0414 0.00971 0.00508 -0.0783 0.9066 0.0153
-3.000 0.0680 0.00873 0.00386 -0.0778 0.8942 0.0161
-2.750 0.0949 0.00807 0.00307 -0.0774 0.8809 0.0175
-2.500 0.1220 0.00786 0.00279 -0.0771 0.8665 0.0189
-2.250 0.1493 0.00772 0.00258 -0.0768 0.8509 0.0208
-2.000 0.1767 0.00761 0.00238 -0.0764 0.8335 0.0222
-1.750 0.2040 0.00720 0.00185 -0.0762 0.8154 0.0263
-1.500 0.2315 0.00713 0.00171 -0.0759 0.7960 0.0293
-1.250 0.2591 0.00702 0.00149 -0.0757 0.7750 0.0324
-1.000 0.2867 0.00694 0.00135 -0.0755 0.7536 0.0385
-0.750 0.3142 0.00697 0.00128 -0.0753 0.7310 0.0417
-0.500 0.3419 0.00688 0.00113 -0.0752 0.7080 0.0505
-0.250 0.3695 0.00690 0.00105 -0.0750 0.6844 0.0563
0.000 0.3972 0.00691 0.00099 -0.0749 0.6606 0.0672
0.250 0.4248 0.00693 0.00096 -0.0748 0.6357 0.0810
0.500 0.4524 0.00696 0.00094 -0.0747 0.6117 0.0971
0.750 0.4800 0.00698 0.00095 -0.0746 0.5869 0.1304
1.000 0.5076 0.00687 0.00099 -0.0747 0.5623 0.2294
1.250 0.5301 0.00522 0.00111 -0.0740 0.5394 1.0000
1.500 0.5576 0.00539 0.00114 -0.0739 0.5156 1.0000
1.750 0.5852 0.00555 0.00118 -0.0738 0.4920 1.0000
2.000 0.6127 0.00571 0.00123 -0.0737 0.4708 1.0000
2.250 0.6402 0.00588 0.00129 -0.0736 0.4493 1.0000
2.500 0.6676 0.00606 0.00136 -0.0735 0.4287 1.0000
2.750 0.6951 0.00622 0.00145 -0.0734 0.4099 1.0000
3.000 0.7224 0.00640 0.00154 -0.0733 0.3915 1.0000
3.250 0.7497 0.00659 0.00163 -0.0733 0.3730 1.0000
3.500 0.7771 0.00676 0.00174 -0.0732 0.3561 1.0000
3.750 0.8044 0.00695 0.00186 -0.0731 0.3402 1.0000
4.000 0.8315 0.00714 0.00199 -0.0730 0.3237 1.0000
4.250 0.8587 0.00734 0.00213 -0.0729 0.3087 1.0000
4.500 0.8857 0.00753 0.00227 -0.0728 0.2945 1.0000
4.750 0.9127 0.00774 0.00244 -0.0727 0.2797 1.0000
5.000 0.9397 0.00795 0.00260 -0.0726 0.2664 1.0000
5.250 0.9662 0.00821 0.00279 -0.0724 0.2488 1.0000
5.500 0.9927 0.00848 0.00298 -0.0723 0.2295 1.0000
5.750 1.0191 0.00873 0.00320 -0.0721 0.2147 1.0000
6.000 1.0453 0.00903 0.00342 -0.0719 0.1973 1.0000
6.250 1.0714 0.00932 0.00366 -0.0718 0.1817 1.0000
6.500 1.0975 0.00962 0.00390 -0.0716 0.1676 1.0000
6.750 1.1232 0.00996 0.00419 -0.0713 0.1509 1.0000
7.000 1.1484 0.01036 0.00451 -0.0710 0.1306 1.0000
7.250 1.1729 0.01087 0.00490 -0.0707 0.1054 1.0000
7.500 1.1956 0.01163 0.00544 -0.0701 0.0700 1.0000
7.750 1.2175 0.01252 0.00613 -0.0694 0.0381 1.0000
8.000 1.2403 0.01325 0.00678 -0.0688 0.0235 1.0000
8.250 1.2642 0.01378 0.00733 -0.0683 0.0188 1.0000
8.500 1.2870 0.01449 0.00808 -0.0675 0.0148 1.0000
8.750 1.3111 0.01494 0.00858 -0.0671 0.0134 1.0000
9.000 1.3341 0.01554 0.00920 -0.0665 0.0116 1.0000
9.250 1.3540 0.01657 0.01038 -0.0653 0.0100 1.0000
9.500 1.3770 0.01709 0.01096 -0.0647 0.0095 1.0000
9.750 1.3990 0.01770 0.01164 -0.0640 0.0088 1.0000
10.000 1.4207 0.01832 0.01231 -0.0633 0.0081 1.0000
10.250 1.4412 0.01905 0.01309 -0.0624 0.0075 1.0000
10.500 1.4561 0.02040 0.01458 -0.0607 0.0068 1.0000
10.750 1.4687 0.02189 0.01623 -0.0588 0.0065 1.0000
11.000 1.4875 0.02261 0.01705 -0.0577 0.0063 1.0000
11.250 1.5045 0.02347 0.01799 -0.0564 0.0060 1.0000
11.500 1.5194 0.02446 0.01908 -0.0549 0.0058 1.0000
11.750 1.5327 0.02551 0.02024 -0.0532 0.0055 1.0000
12.000 1.5440 0.02659 0.02142 -0.0513 0.0052 1.0000
12.250 1.5504 0.02774 0.02265 -0.0486 0.0050 1.0000
12.500 1.5556 0.02900 0.02401 -0.0460 0.0049 1.0000
12.750 1.5586 0.03052 0.02563 -0.0436 0.0047 1.0000
13.000 1.5577 0.03250 0.02772 -0.0414 0.0046 1.0000
13.250 1.5525 0.03509 0.03046 -0.0394 0.0044 1.0000
13.500 1.5417 0.03858 0.03411 -0.0380 0.0043 1.0000
13.750 1.5249 0.04321 0.03894 -0.0374 0.0042 1.0000
14.000 1.5055 0.04869 0.04463 -0.0378 0.0041 1.0000
14.250 1.4868 0.05454 0.05068 -0.0391 0.0041 1.0000
14.500 1.4792 0.05919 0.05549 -0.0406 0.0041 1.0000
14.750 1.4734 0.06379 0.06022 -0.0425 0.0040 1.0000
15.000 1.4626 0.06927 0.06584 -0.0447 0.0040 1.0000
15.250 1.4485 0.07541 0.07212 -0.0472 0.0040 1.0000
15.500 1.4361 0.08143 0.07827 -0.0499 0.0040 1.0000
15.750 1.4197 0.08828 0.08526 -0.0529 0.0040 1.0000
16.000 1.4033 0.09530 0.09241 -0.0561 0.0039 1.0000
16.250 1.3854 0.10271 0.09994 -0.0595 0.0039 1.0000
16.500 1.3671 0.11041 0.10777 -0.0631 0.0040 1.0000
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