FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 200,000 Max Cl/Cd: 73.62 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w121-il-200000-n5.txt Download as CSV file: xf-fx77w121-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2272 0.09120 0.08650 -0.0236 0.5252 0.0243
-9.250 -0.2250 0.08746 0.08274 -0.0248 0.5235 0.0243
-9.000 -0.2229 0.08361 0.07889 -0.0261 0.5217 0.0243
-8.750 -0.2215 0.07970 0.07500 -0.0274 0.5198 0.0243
-8.250 -0.2863 0.08321 0.07819 -0.0328 0.5226 0.0176
-8.000 -0.2854 0.07998 0.07499 -0.0339 0.5203 0.0174
-7.750 -0.2861 0.07683 0.07187 -0.0349 0.5183 0.0171
-7.500 -0.2869 0.07413 0.06917 -0.0354 0.5163 0.0165
-7.250 -0.2922 0.06960 0.06463 -0.0379 0.5149 0.0169
-7.000 -0.2895 0.06599 0.06098 -0.0394 0.5130 0.0164
-6.750 -0.2852 0.06213 0.05704 -0.0409 0.5114 0.0161
-6.500 -0.2805 0.05745 0.05223 -0.0425 0.5100 0.0164
-6.250 -0.2747 0.05045 0.04493 -0.0440 0.5090 0.0177
-6.000 -0.2651 0.04680 0.04111 -0.0436 0.5072 0.0175
-5.750 -0.2546 0.04297 0.03705 -0.0429 0.5053 0.0173
-5.500 -0.2440 0.03861 0.03237 -0.0415 0.5035 0.0172
-5.250 -0.2320 0.03448 0.02784 -0.0398 0.5017 0.0172
-5.000 -0.2185 0.03067 0.02355 -0.0376 0.5001 0.0173
-4.750 -0.2024 0.02743 0.01974 -0.0355 0.4985 0.0175
-4.500 -0.1836 0.02487 0.01663 -0.0337 0.4970 0.0180
-4.250 -0.1621 0.02336 0.01485 -0.0326 0.4955 0.0187
-4.000 -0.1382 0.02286 0.01421 -0.0320 0.4940 0.0201
-3.750 -0.1137 0.02188 0.01300 -0.0312 0.4924 0.0216
-3.500 -0.0885 0.02070 0.01151 -0.0304 0.4906 0.0232
-3.250 -0.0625 0.01967 0.01021 -0.0296 0.4886 0.0241
-3.000 -0.0373 0.01848 0.00889 -0.0290 0.4868 0.0257
-2.750 -0.0114 0.01810 0.00846 -0.0286 0.4851 0.0285
-2.500 0.0147 0.01755 0.00780 -0.0281 0.4836 0.0309
-2.250 0.0407 0.01701 0.00713 -0.0275 0.4823 0.0327
-2.000 0.0655 0.01641 0.00648 -0.0269 0.4811 0.0360
-1.750 0.0910 0.01610 0.00613 -0.0263 0.4799 0.0398
-1.250 0.1417 0.01549 0.00541 -0.0251 0.4771 0.0476
-1.000 0.1675 0.01530 0.00520 -0.0246 0.4754 0.0554
-0.750 0.1930 0.01507 0.00498 -0.0241 0.4738 0.0666
-0.500 0.2180 0.01480 0.00485 -0.0235 0.4725 0.1046
-0.250 0.2402 0.01422 0.00478 -0.0226 0.4712 0.2545
0.000 0.2555 0.01322 0.00474 -0.0204 0.4700 0.5422
0.500 0.4649 0.01273 0.00486 -0.0525 0.4659 1.0000
0.750 0.4901 0.01286 0.00487 -0.0520 0.4647 1.0000
1.000 0.5153 0.01299 0.00494 -0.0515 0.4634 1.0000
1.250 0.5404 0.01313 0.00505 -0.0511 0.4621 1.0000
1.500 0.5656 0.01327 0.00518 -0.0506 0.4607 1.0000
1.750 0.5907 0.01343 0.00531 -0.0501 0.4593 1.0000
2.000 0.6158 0.01359 0.00544 -0.0497 0.4578 1.0000
2.250 0.6410 0.01374 0.00556 -0.0492 0.4561 1.0000
2.500 0.6662 0.01389 0.00569 -0.0488 0.4545 1.0000
2.750 0.6914 0.01406 0.00583 -0.0484 0.4532 1.0000
3.000 0.7167 0.01422 0.00596 -0.0479 0.4518 1.0000
3.250 0.7421 0.01439 0.00607 -0.0475 0.4502 1.0000
3.500 0.7670 0.01459 0.00629 -0.0471 0.4485 1.0000
3.750 0.7916 0.01480 0.00658 -0.0466 0.4465 1.0000
4.000 0.8162 0.01502 0.00686 -0.0461 0.4446 1.0000
4.250 0.8409 0.01522 0.00709 -0.0457 0.4424 1.0000
4.500 0.8657 0.01541 0.00731 -0.0452 0.4405 1.0000
4.750 0.8908 0.01556 0.00749 -0.0448 0.4383 1.0000
5.000 0.9160 0.01571 0.00762 -0.0444 0.4364 1.0000
5.250 0.9411 0.01589 0.00780 -0.0439 0.4342 1.0000
5.500 0.9644 0.01614 0.00820 -0.0434 0.4312 1.0000
5.750 0.9884 0.01637 0.00854 -0.0428 0.4284 1.0000
6.000 1.0127 0.01654 0.00878 -0.0423 0.4256 1.0000
6.250 1.0376 0.01665 0.00893 -0.0419 0.4230 1.0000
6.500 1.0629 0.01677 0.00907 -0.0415 0.4208 1.0000
6.750 1.0860 0.01702 0.00946 -0.0408 0.4176 1.0000
7.000 1.1089 0.01729 0.00988 -0.0402 0.4140 1.0000
7.250 1.1326 0.01750 0.01021 -0.0396 0.4111 1.0000
7.500 1.1568 0.01767 0.01045 -0.0391 0.4085 1.0000
7.750 1.1816 0.01779 0.01064 -0.0387 0.4061 1.0000
8.000 1.2036 0.01808 0.01112 -0.0379 0.4021 1.0000
8.250 1.2256 0.01834 0.01157 -0.0372 0.3977 1.0000
8.500 1.2491 0.01849 0.01184 -0.0366 0.3942 1.0000
8.750 1.2734 0.01854 0.01199 -0.0360 0.3911 1.0000
9.000 1.2931 0.01877 0.01248 -0.0350 0.3824 1.0000
9.250 1.3152 0.01848 0.01232 -0.0340 0.3672 1.0000
9.500 1.3365 0.01825 0.01211 -0.0329 0.3453 1.0000
9.750 1.3532 0.01838 0.01211 -0.0313 0.3120 1.0000
10.000 1.3601 0.01930 0.01279 -0.0287 0.2722 1.0000
10.250 1.3561 0.02099 0.01421 -0.0251 0.2304 1.0000
10.500 1.3431 0.02317 0.01618 -0.0210 0.1937 1.0000
10.750 1.3277 0.02525 0.01820 -0.0169 0.1737 1.0000
11.000 1.3089 0.02874 0.02165 -0.0155 0.1523 1.0000
11.250 1.2868 0.03355 0.02636 -0.0157 0.1276 1.0000
11.500 1.2701 0.03795 0.03070 -0.0159 0.1082 1.0000
11.750 1.2522 0.04244 0.03511 -0.0160 0.0905 1.0000
12.000 1.2270 0.04767 0.04016 -0.0161 0.0626 1.0000
12.250 1.2151 0.05154 0.04397 -0.0161 0.0492 1.0000
12.500 1.2046 0.05530 0.04770 -0.0162 0.0372 1.0000
12.750 1.1907 0.05953 0.05185 -0.0163 0.0261 1.0000
13.000 1.1824 0.06337 0.05570 -0.0166 0.0204 1.0000
13.250 1.1780 0.06686 0.05926 -0.0170 0.0180 1.0000
13.500 1.1764 0.07008 0.06259 -0.0173 0.0161 1.0000
13.750 1.1737 0.07350 0.06608 -0.0177 0.0148 1.0000
14.000 1.1663 0.07765 0.07031 -0.0184 0.0133 1.0000
14.250 1.1630 0.08129 0.07405 -0.0190 0.0129 1.0000
14.500 1.1612 0.08480 0.07770 -0.0196 0.0121 1.0000
14.750 1.1591 0.08841 0.08143 -0.0203 0.0120 1.0000
15.000 1.1549 0.09236 0.08549 -0.0210 0.0113 1.0000
15.250 1.1520 0.09617 0.08939 -0.0219 0.0109 1.0000
15.500 1.1487 0.10008 0.09343 -0.0227 0.0102 1.0000
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