GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 500,000 Max Cl/Cd: 99.04 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe142-il-500000.txt Download as CSV file: xf-goe142-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3941 0.09667 0.09445 -0.0084 1.0000 0.0141
-7.750 -0.3873 0.09349 0.09130 -0.0110 1.0000 0.0150
-7.500 -0.3830 0.09066 0.08851 -0.0146 1.0000 0.0153
-6.500 -0.3454 0.07473 0.07265 -0.0297 1.0000 0.0158
-6.250 -0.3435 0.07151 0.06945 -0.0289 1.0000 0.0162
-6.000 -0.3395 0.06933 0.06729 -0.0278 1.0000 0.0165
-5.750 -0.3361 0.06732 0.06530 -0.0269 1.0000 0.0170
-5.500 -0.3090 0.06361 0.06154 -0.0322 0.9979 0.0181
-5.250 -0.2697 0.05862 0.05648 -0.0408 0.9950 0.0194
-5.000 -0.2166 0.05327 0.05096 -0.0517 0.9911 0.0216
-4.750 -0.1734 0.04853 0.04608 -0.0585 0.9877 0.0218
-4.500 -0.1315 0.04335 0.04073 -0.0648 0.9851 0.0219
-4.250 -0.1007 0.03676 0.03400 -0.0707 0.9817 0.0235
-4.000 -0.0666 0.03425 0.03139 -0.0738 0.9772 0.0250
-3.750 -0.0225 0.03157 0.02844 -0.0770 0.9732 0.0301
-3.500 0.0161 0.02850 0.02506 -0.0793 0.9680 0.0307
-3.250 0.0493 0.01663 0.01211 -0.0819 0.9607 0.0222
-3.000 0.0803 0.01312 0.00801 -0.0826 0.9536 0.0228
-2.750 0.1083 0.01186 0.00655 -0.0824 0.9438 0.0241
-2.500 0.1351 0.01159 0.00623 -0.0819 0.9324 0.0265
-2.250 0.1618 0.01085 0.00532 -0.0812 0.9207 0.0286
-2.000 0.1883 0.01035 0.00468 -0.0805 0.9080 0.0304
-1.750 0.2142 0.00928 0.00347 -0.0798 0.8947 0.0341
-1.500 0.2406 0.00914 0.00328 -0.0791 0.8798 0.0387
-1.250 0.2672 0.00902 0.00307 -0.0785 0.8637 0.0419
-1.000 0.2935 0.00848 0.00247 -0.0780 0.8468 0.0490
-0.750 0.3203 0.00843 0.00231 -0.0774 0.8287 0.0544
-0.500 0.3472 0.00813 0.00197 -0.0770 0.8089 0.0633
-0.250 0.3741 0.00801 0.00178 -0.0766 0.7883 0.0735
0.000 0.4012 0.00793 0.00163 -0.0762 0.7662 0.0861
0.250 0.4282 0.00787 0.00153 -0.0759 0.7436 0.1048
0.500 0.4553 0.00780 0.00146 -0.0756 0.7195 0.1379
0.750 0.4767 0.00613 0.00157 -0.0750 0.6967 0.8041
1.000 0.5047 0.00592 0.00148 -0.0745 0.6714 1.0000
1.250 0.5316 0.00608 0.00147 -0.0741 0.6457 1.0000
1.500 0.5586 0.00626 0.00149 -0.0739 0.6194 1.0000
1.750 0.5856 0.00644 0.00152 -0.0736 0.5931 1.0000
2.000 0.6125 0.00664 0.00157 -0.0733 0.5672 1.0000
2.250 0.6393 0.00684 0.00163 -0.0731 0.5416 1.0000
2.500 0.6661 0.00706 0.00171 -0.0729 0.5164 1.0000
2.750 0.6931 0.00726 0.00181 -0.0727 0.4926 1.0000
3.000 0.7199 0.00748 0.00192 -0.0725 0.4695 1.0000
3.250 0.7467 0.00771 0.00204 -0.0723 0.4468 1.0000
3.500 0.7735 0.00793 0.00217 -0.0721 0.4262 1.0000
3.750 0.8002 0.00817 0.00233 -0.0719 0.4055 1.0000
4.000 0.8269 0.00841 0.00249 -0.0717 0.3857 1.0000
4.250 0.8536 0.00864 0.00266 -0.0716 0.3673 1.0000
4.500 0.8801 0.00890 0.00285 -0.0714 0.3493 1.0000
4.750 0.9065 0.00917 0.00307 -0.0712 0.3320 1.0000
5.000 0.9330 0.00942 0.00329 -0.0710 0.3160 1.0000
5.250 0.9593 0.00969 0.00351 -0.0708 0.3000 1.0000
5.500 0.9856 0.00996 0.00376 -0.0705 0.2850 1.0000
5.750 1.0116 0.01026 0.00403 -0.0703 0.2679 1.0000
6.000 1.0372 0.01061 0.00429 -0.0700 0.2478 1.0000
6.250 1.0630 0.01091 0.00456 -0.0698 0.2306 1.0000
6.500 1.0887 0.01124 0.00486 -0.0695 0.2142 1.0000
6.750 1.1141 0.01160 0.00519 -0.0693 0.1974 1.0000
7.000 1.1392 0.01198 0.00553 -0.0689 0.1807 1.0000
7.250 1.1643 0.01237 0.00590 -0.0686 0.1634 1.0000
7.500 1.1885 0.01287 0.00631 -0.0682 0.1404 1.0000
7.750 1.2117 0.01351 0.00682 -0.0677 0.1099 1.0000
8.000 1.2304 0.01481 0.00776 -0.0667 0.0547 1.0000
8.250 1.2496 0.01605 0.00885 -0.0656 0.0303 1.0000
8.500 1.2705 0.01701 0.00984 -0.0646 0.0235 1.0000
8.750 1.2915 0.01789 0.01084 -0.0637 0.0205 1.0000
9.000 1.3124 0.01873 0.01177 -0.0627 0.0182 1.0000
9.250 1.3292 0.02004 0.01318 -0.0613 0.0161 1.0000
9.500 1.3434 0.02160 0.01493 -0.0594 0.0148 1.0000
9.750 1.3629 0.02240 0.01583 -0.0583 0.0138 1.0000
10.000 1.3794 0.02352 0.01706 -0.0569 0.0129 1.0000
10.250 1.3942 0.02472 0.01837 -0.0553 0.0122 1.0000
10.500 1.4075 0.02601 0.01976 -0.0535 0.0116 1.0000
10.750 1.4173 0.02754 0.02141 -0.0514 0.0110 1.0000
11.000 1.4191 0.02975 0.02375 -0.0484 0.0105 1.0000
11.250 1.4098 0.03304 0.02725 -0.0440 0.0100 1.0000
11.500 1.4197 0.03395 0.02829 -0.0422 0.0098 1.0000
11.750 1.4258 0.03539 0.02990 -0.0402 0.0094 1.0000
12.000 1.4282 0.03735 0.03202 -0.0382 0.0091 1.0000
12.250 1.4281 0.03972 0.03455 -0.0364 0.0089 1.0000
12.500 1.4268 0.04233 0.03733 -0.0351 0.0086 1.0000
12.750 1.4241 0.04526 0.04042 -0.0341 0.0084 1.0000
13.000 1.4198 0.04854 0.04388 -0.0335 0.0083 1.0000
13.250 1.4145 0.05212 0.04763 -0.0335 0.0081 1.0000
13.500 1.4075 0.05614 0.05182 -0.0340 0.0080 1.0000
13.750 1.3989 0.06060 0.05645 -0.0351 0.0079 1.0000
14.000 1.3888 0.06551 0.06154 -0.0366 0.0078 1.0000
14.250 1.3767 0.07098 0.06718 -0.0386 0.0077 1.0000
14.500 1.3627 0.07695 0.07333 -0.0411 0.0077 1.0000
14.750 1.3482 0.08327 0.07981 -0.0440 0.0077 1.0000
15.000 1.3317 0.09020 0.08691 -0.0474 0.0077 1.0000
15.250 1.3137 0.09773 0.09461 -0.0512 0.0077 1.0000
15.500 1.2961 0.10553 0.10257 -0.0554 0.0077 1.0000
15.750 1.2752 0.11431 0.11153 -0.0602 0.0078 1.0000
16.000 1.2524 0.12406 0.12145 -0.0657 0.0079 1.0000
16.250 1.2275 0.13488 0.13244 -0.0720 0.0081 1.0000
16.500 1.2011 0.14673 0.14445 -0.0790 0.0083 1.0000
16.750 1.1744 0.15958 0.15744 -0.0867 0.0086 1.0000
17.000 1.1416 0.17582 0.17379 -0.0963 0.0091 1.0000
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Polar data table (+)
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