GOE 310 (MVA H.42) AIRFOIL (goe310-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 310 (MVA H.42) AIRFOIL (goe310-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.39 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe310-il-1000000-n5.txt Download as CSV file: xf-goe310-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 310 (MVA H.42) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6293 0.02390 0.02106 -0.0919 0.9593 0.0062
-10.000 -0.6059 0.02123 0.01811 -0.0933 0.9527 0.0065
-9.750 -0.5821 0.01934 0.01597 -0.0940 0.9458 0.0069
-9.500 -0.5581 0.01785 0.01424 -0.0942 0.9380 0.0071
-9.250 -0.5351 0.01661 0.01279 -0.0940 0.9305 0.0075
-9.000 -0.5123 0.01557 0.01153 -0.0935 0.9229 0.0079
-8.750 -0.4877 0.01494 0.01080 -0.0931 0.9163 0.0085
-8.500 -0.4627 0.01448 0.01026 -0.0927 0.9094 0.0091
-8.250 -0.4381 0.01397 0.00965 -0.0922 0.9031 0.0098
-8.000 -0.4148 0.01336 0.00890 -0.0915 0.8964 0.0104
-7.500 -0.3640 0.01274 0.00812 -0.0905 0.8839 0.0118
-7.250 -0.3364 0.01285 0.00823 -0.0904 0.8769 0.0125
-7.000 -0.3104 0.01270 0.00803 -0.0900 0.8699 0.0134
-6.750 -0.2865 0.01219 0.00736 -0.0892 0.8618 0.0144
-6.500 -0.2612 0.01188 0.00697 -0.0887 0.8539 0.0149
-6.250 -0.2344 0.01193 0.00697 -0.0884 0.8449 0.0153
-6.000 -0.2082 0.01191 0.00689 -0.0880 0.8335 0.0157
-5.750 -0.1821 0.01193 0.00685 -0.0875 0.8197 0.0163
-5.500 -0.1572 0.01180 0.00661 -0.0869 0.8030 0.0171
-5.250 -0.1329 0.01157 0.00623 -0.0860 0.7838 0.0180
-5.000 -0.1087 0.01138 0.00588 -0.0852 0.7623 0.0187
-4.750 -0.0843 0.01133 0.00568 -0.0844 0.7408 0.0192
-4.500 -0.0594 0.01132 0.00554 -0.0836 0.7203 0.0194
-4.250 -0.0371 0.01065 0.00474 -0.0826 0.7018 0.0201
-4.000 -0.0125 0.01047 0.00448 -0.0819 0.6857 0.0206
-3.750 0.0126 0.01028 0.00422 -0.0813 0.6720 0.0211
-3.500 0.0377 0.01007 0.00394 -0.0806 0.6597 0.0216
-3.250 0.0628 0.00988 0.00366 -0.0800 0.6478 0.0221
-3.000 0.0882 0.00970 0.00342 -0.0794 0.6365 0.0228
-2.750 0.1139 0.00953 0.00319 -0.0789 0.6266 0.0234
-2.500 0.1394 0.00937 0.00296 -0.0784 0.6179 0.0238
-2.250 0.1652 0.00921 0.00274 -0.0779 0.6092 0.0242
-2.000 0.1910 0.00907 0.00256 -0.0774 0.6011 0.0245
-1.750 0.2169 0.00894 0.00238 -0.0769 0.5933 0.0247
-1.500 0.2428 0.00881 0.00222 -0.0765 0.5864 0.0249
-1.250 0.2683 0.00872 0.00207 -0.0759 0.5759 0.0251
-1.000 0.2938 0.00865 0.00194 -0.0754 0.5630 0.0252
-0.750 0.3197 0.00858 0.00185 -0.0749 0.5558 0.0254
-0.500 0.3455 0.00854 0.00176 -0.0744 0.5462 0.0256
-0.250 0.3708 0.00843 0.00160 -0.0738 0.5355 0.0259
0.000 0.3960 0.00835 0.00146 -0.0732 0.5255 0.0265
0.250 0.4216 0.00830 0.00136 -0.0727 0.5164 0.0272
0.500 0.4472 0.00826 0.00130 -0.0722 0.5079 0.0283
0.750 0.4724 0.00829 0.00127 -0.0716 0.4945 0.0291
1.000 0.4971 0.00835 0.00125 -0.0709 0.4737 0.0301
1.250 0.5208 0.00849 0.00125 -0.0701 0.4436 0.0310
1.500 0.5435 0.00871 0.00130 -0.0691 0.4035 0.0317
1.750 0.5640 0.00909 0.00142 -0.0677 0.3446 0.0324
2.000 0.5809 0.00977 0.00169 -0.0657 0.2535 0.0331
2.250 0.6002 0.01028 0.00192 -0.0642 0.1887 0.0367
2.500 0.6193 0.01041 0.00211 -0.0626 0.1486 0.1360
3.000 0.6599 0.01115 0.00264 -0.0598 0.0561 0.1880
3.250 0.6843 0.01128 0.00277 -0.0592 0.0533 0.1938
3.500 0.7086 0.01140 0.00292 -0.0585 0.0513 0.2007
3.750 0.7328 0.01153 0.00306 -0.0578 0.0493 0.2064
4.000 0.7567 0.01165 0.00323 -0.0571 0.0480 0.2149
4.250 0.7805 0.01180 0.00341 -0.0564 0.0468 0.2212
4.500 0.8040 0.01190 0.00358 -0.0556 0.0465 0.2404
4.750 0.8255 0.01188 0.00383 -0.0544 0.0463 0.3626
5.000 0.8480 0.01196 0.00403 -0.0535 0.0459 0.4139
5.500 0.9657 0.01154 0.00494 -0.0684 0.0445 0.9900
5.750 0.9959 0.01179 0.00519 -0.0692 0.0425 0.9936
6.000 1.0317 0.01208 0.00547 -0.0713 0.0409 0.9969
6.250 1.0665 0.01242 0.00580 -0.0733 0.0389 0.9991
6.500 1.0968 0.01269 0.00610 -0.0742 0.0377 1.0000
6.750 1.1179 0.01286 0.00628 -0.0729 0.0368 1.0000
7.000 1.1385 0.01306 0.00649 -0.0716 0.0354 1.0000
7.250 1.1588 0.01326 0.00668 -0.0703 0.0325 1.0000
7.500 1.1784 0.01351 0.00691 -0.0688 0.0283 1.0000
7.750 1.1946 0.01394 0.00722 -0.0668 0.0154 1.0000
8.000 1.2109 0.01435 0.00764 -0.0647 0.0120 1.0000
8.250 1.2279 0.01470 0.00802 -0.0628 0.0109 1.0000
8.500 1.2435 0.01512 0.00846 -0.0606 0.0095 1.0000
8.750 1.2583 0.01557 0.00894 -0.0583 0.0084 1.0000
9.000 1.2731 0.01597 0.00939 -0.0560 0.0079 1.0000
9.250 1.2851 0.01635 0.00980 -0.0532 0.0075 1.0000
9.500 1.2960 0.01676 0.01026 -0.0501 0.0070 1.0000
9.750 1.3074 0.01722 0.01076 -0.0473 0.0067 1.0000
10.000 1.3180 0.01777 0.01134 -0.0445 0.0061 1.0000
10.250 1.3274 0.01844 0.01206 -0.0416 0.0056 1.0000
10.500 1.3396 0.01902 0.01268 -0.0393 0.0054 1.0000
10.750 1.3511 0.01965 0.01339 -0.0370 0.0053 1.0000
11.000 1.3623 0.02034 0.01414 -0.0348 0.0050 1.0000
11.250 1.3724 0.02113 0.01499 -0.0326 0.0049 1.0000
11.500 1.3844 0.02184 0.01574 -0.0307 0.0045 1.0000
11.750 1.3943 0.02271 0.01666 -0.0287 0.0043 1.0000
12.000 1.4027 0.02373 0.01775 -0.0267 0.0042 1.0000
12.250 1.4093 0.02493 0.01901 -0.0245 0.0041 1.0000
12.500 1.4156 0.02620 0.02036 -0.0226 0.0039 1.0000
12.750 1.4197 0.02770 0.02195 -0.0207 0.0037 1.0000
13.000 1.4248 0.02922 0.02355 -0.0190 0.0037 1.0000
13.250 1.4304 0.03075 0.02517 -0.0176 0.0036 1.0000
13.500 1.4341 0.03253 0.02704 -0.0162 0.0036 1.0000
13.750 1.4395 0.03423 0.02883 -0.0151 0.0034 1.0000
14.000 1.4413 0.03635 0.03105 -0.0141 0.0034 1.0000
14.250 1.4451 0.03837 0.03315 -0.0133 0.0033 1.0000
14.500 1.4485 0.04049 0.03536 -0.0127 0.0032 1.0000
14.750 1.4457 0.04334 0.03833 -0.0121 0.0032 1.0000
15.000 1.4482 0.04571 0.04078 -0.0118 0.0031 1.0000
15.250 1.4452 0.04879 0.04397 -0.0116 0.0031 1.0000
15.500 1.4455 0.05154 0.04681 -0.0115 0.0030 1.0000
15.750 1.4413 0.05492 0.05030 -0.0116 0.0030 1.0000
16.000 1.4390 0.05818 0.05365 -0.0118 0.0029 1.0000
16.250 1.4348 0.06171 0.05728 -0.0122 0.0028 1.0000
16.500 1.4317 0.06518 0.06085 -0.0127 0.0028 1.0000
16.750 1.4268 0.06899 0.06476 -0.0134 0.0028 1.0000
17.000 1.4219 0.07290 0.06875 -0.0142 0.0027 1.0000
17.250 1.4174 0.07679 0.07273 -0.0151 0.0026 1.0000
17.500 1.4066 0.08172 0.07778 -0.0164 0.0026 1.0000
17.750 1.4030 0.08567 0.08181 -0.0175 0.0025 1.0000
18.000 1.3873 0.09162 0.08790 -0.0194 0.0026 1.0000
18.250 1.3759 0.09700 0.09339 -0.0212 0.0026 1.0000
18.500 1.3660 0.10224 0.09872 -0.0231 0.0024 1.0000
18.750 1.3538 0.10800 0.10460 -0.0252 0.0024 1.0000
19.000 1.3374 0.11460 0.11134 -0.0279 0.0025 1.0000
19.250 1.3236 0.12084 0.11768 -0.0305 0.0025 1.0000
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