GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.86 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe143-il-1000000.txt Download as CSV file: xf-goe143-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 143 (MVA H.20) 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3735 0.13092 0.12934 -0.0031 1.0000 0.0134
-11.750 -0.3716 0.12739 0.12582 -0.0041 1.0000 0.0135
-8.500 -0.4414 0.09213 0.09056 -0.0084 1.0000 0.0170
-8.250 -0.4340 0.08968 0.08812 -0.0083 1.0000 0.0163
-8.000 -0.4313 0.08585 0.08431 -0.0105 1.0000 0.0158
-7.750 -0.4285 0.08108 0.07955 -0.0146 1.0000 0.0161
-7.500 -0.4210 0.07501 0.07349 -0.0214 1.0000 0.0162
-7.250 -0.4133 0.06584 0.06429 -0.0322 1.0000 0.0165
-7.000 -0.4058 0.05584 0.05421 -0.0425 1.0000 0.0175
-6.750 -0.3853 0.05422 0.05257 -0.0441 0.9993 0.0179
-6.500 -0.3432 0.03343 0.03117 -0.0650 0.9946 0.0216
-6.250 -0.3107 0.03256 0.03025 -0.0672 0.9916 0.0221
-6.000 -0.2787 0.03249 0.03017 -0.0686 0.9871 0.0226
-5.750 -0.2499 0.01600 0.01229 -0.0756 0.9815 0.0276
-5.500 -0.2193 0.01623 0.01254 -0.0760 0.9733 0.0281
-5.250 -0.1902 0.01665 0.01300 -0.0761 0.9633 0.0287
-5.000 -0.1634 0.01674 0.01308 -0.0757 0.9511 0.0294
-4.750 -0.1383 0.01492 0.01095 -0.0753 0.9369 0.0306
-4.500 -0.1128 0.01379 0.00958 -0.0748 0.9205 0.0317
-4.250 -0.0868 0.01331 0.00893 -0.0742 0.9015 0.0323
-4.000 -0.0604 0.01309 0.00856 -0.0736 0.8820 0.0327
-3.750 -0.0345 0.01080 0.00589 -0.0735 0.8648 0.0342
-3.500 -0.0073 0.01062 0.00563 -0.0732 0.8486 0.0350
-3.250 0.0203 0.01044 0.00536 -0.0730 0.8336 0.0358
-3.000 0.0480 0.01006 0.00487 -0.0728 0.8201 0.0364
-2.750 0.0759 0.00970 0.00441 -0.0726 0.8072 0.0371
-2.500 0.1040 0.00937 0.00400 -0.0725 0.7942 0.0380
-2.250 0.1321 0.00908 0.00363 -0.0724 0.7811 0.0388
-2.000 0.1602 0.00886 0.00334 -0.0723 0.7674 0.0397
-1.750 0.1884 0.00879 0.00321 -0.0721 0.7517 0.0404
-1.500 0.2164 0.00842 0.00274 -0.0720 0.7345 0.0414
-1.250 0.2444 0.00799 0.00222 -0.0720 0.7151 0.0430
-1.000 0.2725 0.00786 0.00201 -0.0719 0.6910 0.0443
-0.750 0.3004 0.00781 0.00187 -0.0718 0.6631 0.0458
-0.500 0.3283 0.00782 0.00175 -0.0717 0.6307 0.0474
-0.250 0.3560 0.00788 0.00165 -0.0715 0.5928 0.0490
0.000 0.3837 0.00801 0.00162 -0.0714 0.5517 0.0504
0.250 0.4115 0.00804 0.00150 -0.0714 0.5191 0.0523
0.500 0.4397 0.00802 0.00137 -0.0714 0.4921 0.0561
0.750 0.4677 0.00808 0.00135 -0.0713 0.4689 0.0593
1.000 0.4958 0.00814 0.00134 -0.0713 0.4498 0.0621
1.250 0.5240 0.00817 0.00132 -0.0713 0.4336 0.0671
1.500 0.5521 0.00822 0.00135 -0.0713 0.4176 0.0786
1.750 0.5802 0.00825 0.00140 -0.0713 0.4021 0.1058
2.000 0.6084 0.00796 0.00148 -0.0716 0.3880 0.2930
2.250 0.6313 0.00645 0.00163 -0.0708 0.3770 1.0000
2.500 0.6594 0.00658 0.00169 -0.0708 0.3656 1.0000
3.000 0.7154 0.00686 0.00184 -0.0707 0.3417 1.0000
3.250 0.7433 0.00701 0.00192 -0.0706 0.3286 1.0000
3.500 0.7711 0.00717 0.00202 -0.0706 0.3149 1.0000
3.750 0.7988 0.00734 0.00212 -0.0705 0.3002 1.0000
4.000 0.8264 0.00754 0.00225 -0.0705 0.2844 1.0000
4.250 0.8536 0.00777 0.00239 -0.0704 0.2654 1.0000
4.500 0.8805 0.00807 0.00256 -0.0702 0.2380 1.0000
4.750 0.9055 0.00872 0.00288 -0.0700 0.1782 1.0000
5.000 0.9307 0.00931 0.00323 -0.0697 0.1360 1.0000
5.250 0.9572 0.00964 0.00348 -0.0695 0.1215 1.0000
5.500 0.9838 0.00994 0.00373 -0.0693 0.1128 1.0000
5.750 1.0108 0.01017 0.00395 -0.0692 0.1074 1.0000
6.000 1.0374 0.01044 0.00419 -0.0690 0.1020 1.0000
6.250 1.0640 0.01069 0.00443 -0.0688 0.0965 1.0000
6.500 1.0908 0.01091 0.00465 -0.0687 0.0918 1.0000
6.750 1.1169 0.01122 0.00491 -0.0685 0.0838 1.0000
7.000 1.1424 0.01162 0.00520 -0.0682 0.0657 1.0000
7.250 1.1636 0.01273 0.00608 -0.0674 0.0241 1.0000
7.500 1.1883 0.01324 0.00663 -0.0669 0.0202 1.0000
7.750 1.2134 0.01366 0.00708 -0.0665 0.0183 1.0000
8.000 1.2373 0.01425 0.00771 -0.0659 0.0163 1.0000
8.250 1.2614 0.01478 0.00830 -0.0654 0.0153 1.0000
8.500 1.2857 0.01523 0.00880 -0.0649 0.0145 1.0000
8.750 1.3096 0.01573 0.00934 -0.0644 0.0136 1.0000
9.000 1.3326 0.01632 0.00996 -0.0638 0.0127 1.0000
9.250 1.3523 0.01735 0.01110 -0.0627 0.0117 1.0000
9.500 1.3754 0.01785 0.01165 -0.0621 0.0114 1.0000
9.750 1.3975 0.01845 0.01231 -0.0614 0.0109 1.0000
10.000 1.4188 0.01911 0.01302 -0.0606 0.0104 1.0000
10.250 1.4395 0.01980 0.01377 -0.0597 0.0100 1.0000
10.500 1.4591 0.02055 0.01457 -0.0587 0.0096 1.0000
10.750 1.4756 0.02158 0.01568 -0.0573 0.0092 1.0000
11.000 1.4798 0.02372 0.01799 -0.0544 0.0087 1.0000
11.250 1.4984 0.02435 0.01868 -0.0534 0.0086 1.0000
11.500 1.5148 0.02513 0.01953 -0.0520 0.0084 1.0000
11.750 1.5285 0.02604 0.02051 -0.0504 0.0081 1.0000
12.000 1.5369 0.02707 0.02163 -0.0479 0.0079 1.0000
12.250 1.5426 0.02826 0.02292 -0.0454 0.0077 1.0000
12.500 1.5473 0.02964 0.02439 -0.0431 0.0075 1.0000
12.750 1.5513 0.03121 0.02605 -0.0412 0.0073 1.0000
13.000 1.5544 0.03301 0.02794 -0.0397 0.0072 1.0000
13.250 1.5569 0.03506 0.03008 -0.0386 0.0070 1.0000
13.500 1.5576 0.03750 0.03262 -0.0379 0.0069 1.0000
13.750 1.5559 0.04039 0.03561 -0.0376 0.0068 1.0000
14.000 1.5512 0.04388 0.03921 -0.0378 0.0067 1.0000
14.250 1.5433 0.04802 0.04347 -0.0385 0.0066 1.0000
14.500 1.5320 0.05289 0.04848 -0.0398 0.0065 1.0000
14.750 1.5182 0.05829 0.05401 -0.0414 0.0065 1.0000
15.000 1.5011 0.06428 0.06014 -0.0432 0.0064 1.0000
15.250 1.4820 0.07054 0.06654 -0.0450 0.0063 1.0000
15.500 1.4637 0.07674 0.07287 -0.0468 0.0063 1.0000
15.750 1.4532 0.08216 0.07841 -0.0489 0.0063 1.0000
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Polar data table (+)
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