GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.05 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe234-il-1000000-n5.txt Download as CSV file: xf-goe234-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 234 (MVA CA5) 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5303 0.07523 0.07273 -0.0993 0.9196 0.0192
-14.000 -0.5372 0.07049 0.06788 -0.1027 0.9073 0.0195
-13.750 -0.5414 0.06621 0.06347 -0.1059 0.8898 0.0197
-13.500 -0.5433 0.06234 0.05944 -0.1089 0.8705 0.0200
-13.250 -0.5427 0.05877 0.05573 -0.1119 0.8545 0.0202
-13.000 -0.5394 0.05569 0.05252 -0.1146 0.8432 0.0205
-12.750 -0.5318 0.05269 0.04942 -0.1180 0.8353 0.0207
-12.500 -0.5189 0.04981 0.04643 -0.1220 0.8282 0.0210
-12.250 -0.5024 0.04720 0.04373 -0.1261 0.8229 0.0212
-12.000 -0.4836 0.04456 0.04101 -0.1307 0.8178 0.0215
-11.750 -0.4622 0.04200 0.03839 -0.1356 0.8129 0.0219
-11.250 -0.4119 0.03767 0.03395 -0.1448 0.8048 0.0227
-11.000 -0.3837 0.03583 0.03205 -0.1491 0.8011 0.0231
-10.750 -0.3541 0.03402 0.03018 -0.1536 0.7973 0.0235
-10.500 -0.3232 0.03232 0.02840 -0.1580 0.7935 0.0240
-10.250 -0.2914 0.03085 0.02684 -0.1621 0.7898 0.0244
-10.000 -0.2582 0.02942 0.02534 -0.1663 0.7870 0.0248
-9.750 -0.2240 0.02801 0.02386 -0.1706 0.7837 0.0251
-9.500 -0.1885 0.02667 0.02247 -0.1750 0.7800 0.0255
-9.250 -0.1525 0.02540 0.02115 -0.1794 0.7763 0.0261
-9.000 -0.1166 0.02428 0.01997 -0.1834 0.7728 0.0266
-8.750 -0.0803 0.02321 0.01885 -0.1873 0.7694 0.0270
-8.500 -0.0436 0.02217 0.01777 -0.1911 0.7659 0.0276
-8.250 -0.0073 0.02128 0.01682 -0.1946 0.7621 0.0281
-8.000 0.0291 0.02045 0.01593 -0.1979 0.7581 0.0286
-7.750 0.0655 0.01967 0.01507 -0.2011 0.7538 0.0290
-7.500 0.1021 0.01889 0.01423 -0.2043 0.7499 0.0293
-7.250 0.1398 0.01807 0.01335 -0.2078 0.7453 0.0297
-7.000 0.1789 0.01714 0.01237 -0.2118 0.7406 0.0306
-6.750 0.2158 0.01642 0.01158 -0.2149 0.7355 0.0313
-6.500 0.2524 0.01573 0.01084 -0.2178 0.7306 0.0320
-6.250 0.2888 0.01506 0.01010 -0.2206 0.7241 0.0326
-6.000 0.3246 0.01444 0.00939 -0.2232 0.7178 0.0333
-5.750 0.3600 0.01386 0.00875 -0.2255 0.7118 0.0339
-5.500 0.3948 0.01333 0.00813 -0.2277 0.7042 0.0345
-5.250 0.4312 0.01263 0.00734 -0.2304 0.6966 0.0357
-5.000 0.4656 0.01212 0.00677 -0.2324 0.6875 0.0370
-4.750 0.4992 0.01167 0.00624 -0.2341 0.6793 0.0384
-4.500 0.5322 0.01129 0.00577 -0.2355 0.6709 0.0397
-4.250 0.5653 0.01087 0.00526 -0.2371 0.6629 0.0413
-4.000 0.5979 0.01049 0.00483 -0.2384 0.6540 0.0435
-3.750 0.6295 0.01023 0.00448 -0.2394 0.6447 0.0458
-3.500 0.6607 0.01002 0.00419 -0.2402 0.6347 0.0484
-3.250 0.6916 0.00987 0.00399 -0.2410 0.6257 0.0519
-3.000 0.7220 0.00979 0.00383 -0.2415 0.6171 0.0554
-2.750 0.7526 0.00967 0.00368 -0.2421 0.6089 0.0602
-2.500 0.7827 0.00963 0.00356 -0.2426 0.5997 0.0645
-2.250 0.8130 0.00954 0.00344 -0.2431 0.5925 0.0712
-2.000 0.8434 0.00944 0.00330 -0.2436 0.5850 0.0831
-1.750 0.8753 0.00907 0.00302 -0.2448 0.5774 0.1552
-1.500 0.9065 0.00874 0.00280 -0.2458 0.5670 0.2333
-1.250 0.9354 0.00882 0.00285 -0.2460 0.5555 0.2542
-1.000 0.9639 0.00893 0.00292 -0.2460 0.5442 0.2655
-0.750 0.9929 0.00900 0.00296 -0.2461 0.5378 0.2707
-0.500 1.0218 0.00908 0.00303 -0.2462 0.5315 0.2758
-0.250 1.0503 0.00919 0.00309 -0.2462 0.5248 0.2794
0.000 1.0791 0.00927 0.00314 -0.2463 0.5181 0.2825
0.250 1.1074 0.00939 0.00323 -0.2463 0.5099 0.2866
0.500 1.1358 0.00950 0.00333 -0.2463 0.5029 0.2898
0.750 1.1640 0.00962 0.00342 -0.2463 0.4950 0.2933
1.000 1.1920 0.00975 0.00351 -0.2463 0.4880 0.2948
1.250 1.2202 0.00986 0.00359 -0.2462 0.4799 0.2961
1.500 1.2478 0.01001 0.00369 -0.2462 0.4716 0.2975
1.750 1.2756 0.01014 0.00379 -0.2461 0.4625 0.2986
2.000 1.3029 0.01031 0.00391 -0.2459 0.4529 0.3004
2.250 1.3300 0.01048 0.00405 -0.2458 0.4415 0.3019
2.500 1.3569 0.01068 0.00421 -0.2456 0.4298 0.3035
2.750 1.3831 0.01092 0.00440 -0.2452 0.4162 0.3057
3.000 1.4081 0.01125 0.00463 -0.2447 0.3959 0.3079
3.250 1.4317 0.01170 0.00493 -0.2440 0.3703 0.3094
3.500 1.4555 0.01210 0.00521 -0.2433 0.3477 0.3107
3.750 1.4794 0.01246 0.00548 -0.2426 0.3303 0.3118
4.000 1.5031 0.01283 0.00577 -0.2418 0.3149 0.3129
4.250 1.5266 0.01319 0.00605 -0.2411 0.3009 0.3138
4.500 1.5492 0.01358 0.00637 -0.2401 0.2859 0.3147
5.000 1.5944 0.01430 0.00700 -0.2383 0.2613 0.3177
5.250 1.6165 0.01466 0.00732 -0.2373 0.2532 0.3191
5.500 1.6394 0.01493 0.00760 -0.2364 0.2478 0.3205
5.750 1.6613 0.01523 0.00790 -0.2353 0.2422 0.3219
6.250 1.7017 0.01594 0.00859 -0.2326 0.2293 0.3247
6.500 1.7191 0.01639 0.00901 -0.2307 0.2213 0.3262
6.750 1.7360 0.01677 0.00940 -0.2287 0.2162 0.3276
7.000 1.7514 0.01714 0.00978 -0.2264 0.2130 0.3287
7.250 1.7683 0.01757 0.01023 -0.2245 0.2093 0.3296
7.500 1.7840 0.01811 0.01077 -0.2224 0.2041 0.3306
7.750 1.8009 0.01861 0.01129 -0.2207 0.1988 0.3322
8.000 1.8165 0.01919 0.01188 -0.2187 0.1920 0.3336
8.250 1.8306 0.01989 0.01257 -0.2166 0.1849 0.3349
8.500 1.8428 0.02072 0.01336 -0.2143 0.1731 0.3361
8.750 1.8376 0.02268 0.01507 -0.2095 0.1337 0.3370
9.000 1.8267 0.02516 0.01735 -0.2043 0.0992 0.3377
9.250 1.8279 0.02694 0.01906 -0.2010 0.0824 0.3388
9.500 1.8205 0.02947 0.02143 -0.1968 0.0522 0.3396
9.750 1.8189 0.03167 0.02357 -0.1935 0.0354 0.3407
10.000 1.8274 0.03311 0.02505 -0.1915 0.0322 0.3421
10.250 1.8366 0.03451 0.02648 -0.1897 0.0306 0.3434
10.500 1.8450 0.03601 0.02803 -0.1878 0.0292 0.3444
10.750 1.8533 0.03755 0.02961 -0.1860 0.0279 0.3453
11.000 1.8631 0.03897 0.03108 -0.1844 0.0273 0.3461
11.250 1.8714 0.04056 0.03274 -0.1827 0.0266 0.3475
11.500 1.8793 0.04220 0.03444 -0.1811 0.0258 0.3488
11.750 1.8860 0.04401 0.03631 -0.1794 0.0251 0.3501
12.000 1.8921 0.04591 0.03827 -0.1778 0.0243 0.3513
12.250 1.8972 0.04796 0.04038 -0.1762 0.0235 0.3524
12.500 1.9033 0.04995 0.04244 -0.1747 0.0230 0.3537
12.750 1.9102 0.05185 0.04441 -0.1734 0.0225 0.3551
13.000 1.9155 0.05398 0.04660 -0.1720 0.0220 0.3565
13.250 1.9204 0.05617 0.04886 -0.1707 0.0214 0.3579
13.500 1.9245 0.05851 0.05126 -0.1694 0.0208 0.3591
13.750 1.9273 0.06105 0.05386 -0.1682 0.0201 0.3602
14.000 1.9289 0.06374 0.05662 -0.1670 0.0195 0.3610
14.250 1.9315 0.06634 0.05929 -0.1660 0.0189 0.3618
14.500 1.9341 0.06902 0.06204 -0.1650 0.0185 0.3632
14.750 1.9361 0.07177 0.06487 -0.1641 0.0179 0.3645
15.000 1.9373 0.07465 0.06783 -0.1632 0.0174 0.3656
15.250 1.9371 0.07777 0.07102 -0.1624 0.0168 0.3668
15.500 1.9363 0.08095 0.07427 -0.1616 0.0163 0.3680
15.750 1.9343 0.08430 0.07770 -0.1609 0.0157 0.3692
16.000 1.9326 0.08767 0.08115 -0.1604 0.0154 0.3704
16.250 1.9311 0.09103 0.08459 -0.1599 0.0149 0.3718
16.500 1.9288 0.09452 0.08816 -0.1594 0.0143 0.3732
16.750 1.9251 0.09826 0.09198 -0.1591 0.0138 0.3744
17.000 1.9211 0.10202 0.09581 -0.1589 0.0133 0.3755
17.250 1.9164 0.10590 0.09977 -0.1588 0.0129 0.3764
17.500 1.9109 0.10998 0.10393 -0.1589 0.0126 0.3771
17.750 1.9066 0.11389 0.10794 -0.1590 0.0123 0.3784
18.000 1.9023 0.11783 0.11198 -0.1593 0.0120 0.3796
18.250 1.8965 0.12205 0.11629 -0.1598 0.0116 0.3808
18.500 1.8909 0.12627 0.12059 -0.1604 0.0113 0.3819
18.750 1.8854 0.13043 0.12483 -0.1611 0.0110 0.3831
19.000 1.8787 0.13488 0.12937 -0.1621 0.0107 0.3842
19.250 1.8720 0.13938 0.13396 -0.1632 0.0104 0.3854
|
Polar data table (+)
Polar graphs
<< Back to GOE 234 (MVA CA5) AIRFOIL (goe234-il)