FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 500,000 Max Cl/Cd: 114.35 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w121-il-500000-n5.txt Download as CSV file: xf-fx77w121-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-121
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2840 0.08566 0.08150 -0.0314 0.4726 0.0086
-8.500 -0.2829 0.08228 0.07814 -0.0329 0.4715 0.0085
-8.250 -0.2837 0.07874 0.07462 -0.0345 0.4701 0.0083
-8.000 -0.2906 0.07456 0.07048 -0.0367 0.4692 0.0085
-7.750 -0.3001 0.07089 0.06685 -0.0381 0.4684 0.0083
-7.500 -0.3042 0.06746 0.06340 -0.0394 0.4673 0.0079
-7.250 -0.3109 0.06172 0.05763 -0.0422 0.4667 0.0084
-7.000 -0.3106 0.05685 0.05269 -0.0438 0.4657 0.0082
-6.500 -0.3080 0.04512 0.04063 -0.0449 0.4638 0.0084
-6.250 -0.3534 0.02422 0.01832 -0.0374 0.4649 0.0092
-6.000 -0.3394 0.02122 0.01478 -0.0351 0.4636 0.0094
-5.750 -0.3222 0.01893 0.01208 -0.0332 0.4623 0.0097
-5.500 -0.2974 0.01871 0.01182 -0.0327 0.4607 0.0102
-5.250 -0.2737 0.01794 0.01089 -0.0319 0.4593 0.0106
-5.000 -0.2504 0.01693 0.00965 -0.0309 0.4580 0.0109
-4.750 -0.2261 0.01615 0.00871 -0.0301 0.4567 0.0115
-4.500 -0.2017 0.01534 0.00770 -0.0292 0.4555 0.0120
-4.250 -0.1766 0.01473 0.00693 -0.0285 0.4542 0.0127
-4.000 -0.1518 0.01414 0.00620 -0.0277 0.4530 0.0134
-3.750 -0.1269 0.01367 0.00565 -0.0271 0.4516 0.0139
-3.500 -0.1009 0.01345 0.00538 -0.0266 0.4503 0.0149
-3.250 -0.0746 0.01330 0.00518 -0.0262 0.4491 0.0163
-3.000 -0.0485 0.01302 0.00484 -0.0257 0.4483 0.0175
-2.750 -0.0233 0.01260 0.00438 -0.0250 0.4474 0.0190
-2.500 0.0027 0.01237 0.00412 -0.0245 0.4464 0.0203
-2.250 0.0289 0.01218 0.00390 -0.0241 0.4455 0.0221
-2.000 0.0555 0.01206 0.00374 -0.0237 0.4445 0.0240
-1.750 0.0809 0.01175 0.00339 -0.0231 0.4434 0.0263
-1.500 0.1071 0.01158 0.00320 -0.0227 0.4423 0.0285
-1.250 0.1336 0.01145 0.00305 -0.0223 0.4410 0.0315
-1.000 0.1601 0.01135 0.00290 -0.0219 0.4400 0.0336
-0.750 0.1863 0.01120 0.00273 -0.0215 0.4392 0.0387
-0.500 0.2128 0.01112 0.00264 -0.0211 0.4382 0.0454
-0.250 0.2390 0.01101 0.00256 -0.0207 0.4373 0.0630
0.000 0.2647 0.01084 0.00251 -0.0203 0.4365 0.1067
0.250 0.2893 0.01059 0.00249 -0.0197 0.4355 0.1952
0.500 0.3117 0.01014 0.00250 -0.0188 0.4344 0.3559
0.750 0.3308 0.00954 0.00250 -0.0171 0.4337 0.5539
1.000 0.5063 0.00895 0.00296 -0.0490 0.4318 0.9948
1.250 0.5555 0.00897 0.00292 -0.0537 0.4307 1.0000
1.500 0.5809 0.00902 0.00294 -0.0532 0.4298 1.0000
1.750 0.6064 0.00908 0.00297 -0.0527 0.4288 1.0000
2.000 0.6319 0.00913 0.00300 -0.0523 0.4277 1.0000
2.250 0.6574 0.00919 0.00303 -0.0519 0.4262 1.0000
2.500 0.6830 0.00925 0.00307 -0.0514 0.4250 1.0000
2.750 0.7085 0.00931 0.00311 -0.0510 0.4235 1.0000
3.000 0.7341 0.00939 0.00317 -0.0506 0.4222 1.0000
3.250 0.7596 0.00950 0.00324 -0.0502 0.4210 1.0000
3.500 0.7851 0.00961 0.00334 -0.0498 0.4197 1.0000
3.750 0.8108 0.00966 0.00343 -0.0494 0.4183 1.0000
4.000 0.8363 0.00971 0.00352 -0.0490 0.4165 1.0000
4.250 0.8619 0.00977 0.00360 -0.0486 0.4144 1.0000
4.500 0.8874 0.00983 0.00370 -0.0482 0.4122 1.0000
4.750 0.9129 0.00991 0.00379 -0.0478 0.4105 1.0000
5.000 0.9383 0.00998 0.00386 -0.0474 0.4081 1.0000
5.250 0.9635 0.01008 0.00395 -0.0470 0.4056 1.0000
5.500 0.9889 0.01017 0.00410 -0.0466 0.4037 1.0000
5.750 1.0144 0.01025 0.00426 -0.0463 0.4019 1.0000
6.000 1.0398 0.01035 0.00441 -0.0459 0.4000 1.0000
6.250 1.0651 0.01044 0.00457 -0.0455 0.3978 1.0000
6.500 1.0904 0.01053 0.00472 -0.0452 0.3957 1.0000
6.750 1.1156 0.01062 0.00484 -0.0447 0.3931 1.0000
7.000 1.1405 0.01074 0.00499 -0.0443 0.3909 1.0000
7.250 1.1656 0.01083 0.00520 -0.0440 0.3880 1.0000
7.500 1.1908 0.01093 0.00541 -0.0436 0.3847 1.0000
7.750 1.2157 0.01101 0.00556 -0.0432 0.3804 1.0000
8.000 1.2406 0.01105 0.00567 -0.0428 0.3726 1.0000
8.250 1.2647 0.01106 0.00568 -0.0422 0.3541 1.0000
8.500 1.2855 0.01137 0.00588 -0.0413 0.3247 1.0000
8.750 1.2998 0.01228 0.00653 -0.0396 0.2790 1.0000
9.000 1.3097 0.01358 0.00756 -0.0374 0.2290 1.0000
9.250 1.3176 0.01496 0.00870 -0.0350 0.1844 1.0000
9.500 1.3201 0.01662 0.01007 -0.0320 0.1352 1.0000
9.750 1.3132 0.01868 0.01184 -0.0280 0.0864 1.0000
10.000 1.3073 0.02050 0.01352 -0.0242 0.0569 1.0000
10.250 1.2931 0.02229 0.01528 -0.0195 0.0408 1.0000
10.500 1.2761 0.02569 0.01869 -0.0181 0.0251 1.0000
10.750 1.2712 0.02899 0.02204 -0.0185 0.0187 1.0000
11.000 1.2692 0.03205 0.02516 -0.0188 0.0149 1.0000
11.250 1.2669 0.03508 0.02826 -0.0189 0.0127 1.0000
11.500 1.2671 0.03777 0.03103 -0.0189 0.0117 1.0000
11.750 1.2623 0.04095 0.03426 -0.0189 0.0098 1.0000
12.000 1.2588 0.04399 0.03737 -0.0189 0.0080 1.0000
12.250 1.2588 0.04664 0.04011 -0.0188 0.0083 1.0000
12.500 1.2590 0.04928 0.04282 -0.0188 0.0079 1.0000
12.750 1.2549 0.05238 0.04597 -0.0188 0.0069 1.0000
13.000 1.2489 0.05575 0.04942 -0.0188 0.0062 1.0000
13.250 1.2505 0.05840 0.05213 -0.0190 0.0058 1.0000
13.500 1.2502 0.06133 0.05514 -0.0192 0.0056 1.0000
13.750 1.2497 0.06436 0.05825 -0.0196 0.0055 1.0000
14.000 1.2499 0.06733 0.06129 -0.0199 0.0048 1.0000
14.250 1.2495 0.07041 0.06447 -0.0203 0.0048 1.0000
14.500 1.2471 0.07381 0.06792 -0.0208 0.0043 1.0000
14.750 1.2484 0.07679 0.07100 -0.0212 0.0046 1.0000
15.000 1.2447 0.08047 0.07476 -0.0218 0.0045 1.0000
15.250 1.2412 0.08416 0.07851 -0.0225 0.0042 1.0000
15.500 1.2371 0.08803 0.08247 -0.0233 0.0040 1.0000
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Polar data table (+)
Polar graphs
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