WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Reynolds number: 100,000 Max Cl/Cd: 55.11 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx62k131-il-100000-n5.txt Download as CSV file: xf-fx62k131-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 62-K-131 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2537 0.09882 0.09411 -0.0833 0.9617 0.0499
-8.750 -0.1346 0.06802 0.06343 -0.0981 0.9361 0.0247
-8.250 -0.2250 0.07508 0.07033 -0.1008 0.9400 0.0251
-8.000 -0.2193 0.07033 0.06555 -0.1051 0.9355 0.0241
-7.750 -0.2249 0.06632 0.06150 -0.1079 0.9263 0.0235
-7.500 -0.2193 0.06092 0.05596 -0.1145 0.9212 0.0227
-7.250 -0.2230 0.05743 0.05232 -0.1158 0.9125 0.0221
-7.000 -0.2120 0.05256 0.04717 -0.1199 0.9082 0.0212
-6.750 -0.2092 0.04914 0.04349 -0.1201 0.9007 0.0205
-6.500 -0.1929 0.04482 0.03877 -0.1224 0.8965 0.0197
-6.250 -0.1673 0.04031 0.03371 -0.1254 0.8939 0.0189
-6.000 -0.1541 0.03760 0.03058 -0.1247 0.8876 0.0186
-5.750 -0.1280 0.03483 0.02737 -0.1261 0.8842 0.0189
-5.500 -0.0969 0.03277 0.02498 -0.1281 0.8820 0.0208
-5.250 -0.0624 0.03060 0.02232 -0.1301 0.8803 0.0229
-5.000 -0.0398 0.02895 0.02034 -0.1295 0.8759 0.0235
-4.750 -0.0149 0.02743 0.01853 -0.1290 0.8720 0.0241
-4.500 0.0146 0.02600 0.01686 -0.1292 0.8694 0.0250
-4.250 0.0456 0.02469 0.01542 -0.1296 0.8674 0.0263
-4.000 0.0781 0.02341 0.01416 -0.1311 0.8657 0.0316
-3.750 0.0964 0.02297 0.01363 -0.1298 0.8599 0.0350
-3.500 0.1284 0.02213 0.01265 -0.1311 0.8567 0.0400
-3.250 0.1643 0.02135 0.01183 -0.1333 0.8544 0.0588
-3.000 0.2079 0.01881 0.01160 -0.1385 0.8534 0.5498
-2.500 0.2159 0.02112 0.01418 -0.1246 0.8419 0.7278
-2.250 0.2359 0.02155 0.01442 -0.1217 0.8389 0.7481
-2.000 0.2587 0.02174 0.01443 -0.1208 0.8342 0.7567
-1.750 0.2803 0.02191 0.01445 -0.1198 0.8290 0.7637
-1.500 0.3120 0.02190 0.01425 -0.1207 0.8262 0.7718
-1.250 0.3422 0.02183 0.01401 -0.1210 0.8239 0.7779
-1.000 0.3596 0.02218 0.01429 -0.1196 0.8170 0.7852
-0.750 0.3869 0.02220 0.01420 -0.1196 0.8133 0.7910
-0.500 0.4175 0.02213 0.01402 -0.1201 0.8108 0.7971
-0.250 0.4393 0.02238 0.01420 -0.1196 0.8048 0.8035
0.000 0.4622 0.02246 0.01424 -0.1188 0.8000 0.8086
0.250 0.4971 0.02238 0.01407 -0.1205 0.7974 0.8142
0.750 0.5420 0.02266 0.01431 -0.1191 0.7864 0.8234
1.000 0.5773 0.02255 0.01415 -0.1208 0.7835 0.8281
1.500 0.6225 0.02281 0.01445 -0.1195 0.7720 0.8362
1.750 0.6569 0.02266 0.01428 -0.1209 0.7691 0.8403
2.000 0.6777 0.02298 0.01463 -0.1203 0.7616 0.8445
2.250 0.7044 0.02289 0.01457 -0.1201 0.7570 0.8481
2.500 0.7387 0.02263 0.01436 -0.1212 0.7542 0.8517
2.750 0.7584 0.02304 0.01483 -0.1205 0.7449 0.8562
3.000 0.7905 0.02273 0.01456 -0.1211 0.7412 0.8594
3.250 0.8074 0.02298 0.01490 -0.1195 0.7320 0.8634
3.500 0.8419 0.02267 0.01469 -0.1207 0.7277 0.8669
3.750 0.8643 0.02294 0.01505 -0.1203 0.7187 0.8710
4.000 0.8940 0.02262 0.01482 -0.1204 0.7139 0.8742
4.250 0.9126 0.02286 0.01518 -0.1191 0.7045 0.8782
4.500 0.9476 0.02254 0.01500 -0.1203 0.6997 0.8816
4.750 0.9676 0.02281 0.01541 -0.1194 0.6896 0.8855
5.000 0.9980 0.02247 0.01519 -0.1196 0.6837 0.8888
5.250 1.0186 0.02261 0.01548 -0.1186 0.6735 0.8927
5.500 1.0410 0.02275 0.01582 -0.1179 0.6631 0.8967
5.750 1.0680 0.02256 0.01578 -0.1176 0.6542 0.9002
6.000 1.0949 0.02230 0.01567 -0.1172 0.6438 0.9040
6.250 1.1155 0.02224 0.01575 -0.1159 0.6269 0.9081
6.500 1.1390 0.02204 0.01566 -0.1148 0.6052 0.9121
6.750 1.1606 0.02185 0.01554 -0.1133 0.5821 0.9163
7.000 1.1859 0.02175 0.01555 -0.1126 0.5584 0.9204
7.250 1.2081 0.02192 0.01577 -0.1116 0.5299 0.9247
7.500 1.2222 0.02226 0.01610 -0.1092 0.4961 0.9297
7.750 1.2334 0.02288 0.01661 -0.1066 0.4507 0.9351
8.000 1.2385 0.02384 0.01735 -0.1032 0.3972 0.9409
8.250 1.2380 0.02520 0.01842 -0.0995 0.3402 0.9477
8.500 1.2358 0.02680 0.01974 -0.0959 0.2852 0.9554
9.000 1.2292 0.03058 0.02299 -0.0896 0.1803 0.9845
9.250 1.2311 0.03280 0.02505 -0.0878 0.1368 0.9999
9.500 1.2327 0.03527 0.02729 -0.0861 0.0973 0.9999
10.000 1.2351 0.04044 0.03197 -0.0832 0.0411 0.9999
10.250 1.2388 0.04293 0.03446 -0.0819 0.0292 0.9999
10.500 1.2411 0.04559 0.03725 -0.0805 0.0230 0.9999
10.750 1.2403 0.04859 0.04039 -0.0790 0.0197 0.9999
11.000 1.2430 0.05128 0.04328 -0.0778 0.0170 0.9999
11.250 1.2460 0.05396 0.04610 -0.0770 0.0149 0.9999
11.500 1.2427 0.05730 0.04952 -0.0758 0.0134 0.9999
11.750 1.2488 0.05980 0.05226 -0.0751 0.0123 0.9999
12.000 1.2528 0.06259 0.05525 -0.0742 0.0114 0.9999
12.250 1.2567 0.06543 0.05828 -0.0734 0.0109 0.9999
12.500 1.2610 0.06832 0.06137 -0.0725 0.0103 0.9999
12.750 1.2654 0.07131 0.06455 -0.0718 0.0099 0.9999
13.000 1.2689 0.07445 0.06796 -0.0712 0.0096 0.9999
13.250 1.2708 0.07781 0.07154 -0.0708 0.0094 0.9999
13.500 1.2711 0.08145 0.07541 -0.0706 0.0092 0.9999
13.750 1.2692 0.08545 0.07965 -0.0706 0.0090 0.9999
14.000 1.2652 0.08977 0.08421 -0.0710 0.0088 0.9999
14.250 1.2593 0.09453 0.08922 -0.0717 0.0087 0.9999
14.500 1.2517 0.09960 0.09455 -0.0729 0.0087 0.9999
14.750 1.2422 0.10517 0.10038 -0.0747 0.0086 0.9999
15.000 1.2313 0.11129 0.10675 -0.0772 0.0086 0.9999
15.250 1.2194 0.11779 0.11351 -0.0803 0.0086 0.9999
15.500 1.2064 0.12494 0.12093 -0.0842 0.0086 0.9999
15.750 1.1921 0.13289 0.12913 -0.0891 0.0087 0.9999
16.000 1.1762 0.14182 0.13831 -0.0950 0.0088 0.9999
16.250 1.1583 0.15231 0.14904 -0.1023 0.0090 0.9999
16.500 1.1366 0.16549 0.16244 -0.1117 0.0093 0.9999
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