FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 1,000,000 Max Cl/Cd: 149.16 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w121-il-1000000.txt Download as CSV file: xf-fx77w121-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2672 0.08641 0.08294 -0.0335 0.4727 0.0107
-8.500 -0.2625 0.08346 0.08000 -0.0351 0.4722 0.0122
-8.250 -0.2620 0.07979 0.07635 -0.0372 0.4703 0.0125
-8.000 -0.2636 0.07645 0.07303 -0.0383 0.4694 0.0112
-7.250 -0.2763 0.06437 0.06097 -0.0452 0.4670 0.0130
-7.000 -0.2737 0.06024 0.05680 -0.0466 0.4656 0.0130
-6.750 -0.2686 0.05625 0.05274 -0.0475 0.4642 0.0130
-6.500 -0.2634 0.05154 0.04794 -0.0480 0.4637 0.0130
-6.250 -0.2597 0.04576 0.04201 -0.0477 0.4635 0.0131
-6.000 -0.2509 0.04161 0.03771 -0.0468 0.4627 0.0131
-5.750 -0.2423 0.03734 0.03325 -0.0453 0.4620 0.0131
-5.500 -0.2521 0.03000 0.02552 -0.0416 0.4616 0.0118
-5.250 -0.2701 0.01789 0.01211 -0.0330 0.4614 0.0111
-5.000 -0.2491 0.01641 0.01037 -0.0315 0.4602 0.0114
-4.750 -0.2269 0.01502 0.00873 -0.0302 0.4590 0.0117
-4.500 -0.2024 0.01429 0.00786 -0.0293 0.4579 0.0121
-4.250 -0.1769 0.01383 0.00729 -0.0287 0.4568 0.0127
-4.000 -0.1536 0.01268 0.00594 -0.0275 0.4558 0.0135
-3.750 -0.1295 0.01201 0.00517 -0.0266 0.4548 0.0141
-3.500 -0.1032 0.01182 0.00496 -0.0262 0.4537 0.0151
-3.250 -0.0768 0.01167 0.00477 -0.0257 0.4525 0.0162
-3.000 -0.0510 0.01140 0.00444 -0.0252 0.4514 0.0172
-2.750 -0.0263 0.01104 0.00399 -0.0244 0.4497 0.0186
-2.500 -0.0009 0.01070 0.00364 -0.0237 0.4490 0.0202
-2.250 0.0257 0.01055 0.00348 -0.0233 0.4484 0.0218
-2.000 0.0530 0.01051 0.00344 -0.0231 0.4477 0.0238
-1.750 0.0783 0.01019 0.00306 -0.0224 0.4470 0.0255
-1.500 0.1041 0.00995 0.00282 -0.0219 0.4463 0.0285
-1.250 0.1307 0.00984 0.00269 -0.0215 0.4454 0.0312
-1.000 0.1576 0.00975 0.00258 -0.0212 0.4445 0.0330
-0.750 0.1836 0.00956 0.00235 -0.0206 0.4436 0.0373
-0.500 0.2103 0.00946 0.00225 -0.0203 0.4426 0.0433
-0.250 0.2367 0.00933 0.00215 -0.0199 0.4415 0.0570
0.000 0.2612 0.00902 0.00210 -0.0192 0.4407 0.1430
0.250 0.2835 0.00854 0.00208 -0.0182 0.4398 0.3069
0.500 0.3006 0.00779 0.00209 -0.0162 0.4389 0.5668
0.750 0.4146 0.00712 0.00249 -0.0351 0.4374 0.9800
1.000 0.4735 0.00741 0.00269 -0.0418 0.4358 0.9877
1.250 0.5526 0.00761 0.00280 -0.0530 0.4345 0.9973
1.500 0.5966 0.00751 0.00268 -0.0565 0.4333 1.0000
1.750 0.6220 0.00754 0.00270 -0.0560 0.4324 1.0000
2.000 0.6475 0.00757 0.00271 -0.0555 0.4314 1.0000
2.250 0.6730 0.00760 0.00274 -0.0551 0.4303 1.0000
2.500 0.6985 0.00764 0.00277 -0.0546 0.4291 1.0000
2.750 0.7242 0.00768 0.00280 -0.0542 0.4279 1.0000
3.000 0.7498 0.00771 0.00281 -0.0538 0.4262 1.0000
3.250 0.7755 0.00775 0.00283 -0.0534 0.4247 1.0000
3.500 0.8010 0.00781 0.00289 -0.0530 0.4230 1.0000
3.750 0.8262 0.00800 0.00304 -0.0525 0.4200 1.0000
4.000 0.8521 0.00800 0.00306 -0.0522 0.4190 1.0000
4.250 0.8779 0.00801 0.00310 -0.0518 0.4177 1.0000
4.500 0.9037 0.00802 0.00314 -0.0514 0.4160 1.0000
4.750 0.9296 0.00806 0.00320 -0.0511 0.4145 1.0000
5.000 0.9553 0.00811 0.00327 -0.0508 0.4130 1.0000
5.250 0.9811 0.00816 0.00334 -0.0504 0.4116 1.0000
5.500 1.0068 0.00822 0.00342 -0.0501 0.4100 1.0000
5.750 1.0325 0.00829 0.00350 -0.0497 0.4083 1.0000
6.000 1.0577 0.00844 0.00365 -0.0494 0.4057 1.0000
6.250 1.0834 0.00850 0.00377 -0.0490 0.4042 1.0000
6.500 1.1091 0.00853 0.00386 -0.0487 0.4027 1.0000
6.750 1.1349 0.00856 0.00395 -0.0484 0.4007 1.0000
7.000 1.1606 0.00857 0.00400 -0.0481 0.3978 1.0000
7.500 1.2119 0.00853 0.00403 -0.0475 0.3879 1.0000
7.750 1.2380 0.00848 0.00403 -0.0472 0.3803 1.0000
8.000 1.2634 0.00847 0.00399 -0.0469 0.3633 1.0000
8.250 1.2871 0.00867 0.00413 -0.0464 0.3416 1.0000
8.500 1.3079 0.00913 0.00448 -0.0455 0.3114 1.0000
8.750 1.3253 0.00988 0.00505 -0.0441 0.2742 1.0000
9.000 1.3399 0.01087 0.00581 -0.0424 0.2314 1.0000
9.250 1.3506 0.01213 0.00678 -0.0402 0.1828 1.0000
9.500 1.3569 0.01362 0.00795 -0.0375 0.1296 1.0000
9.750 1.3477 0.01599 0.00988 -0.0328 0.0599 1.0000
10.000 1.3434 0.01775 0.01146 -0.0288 0.0260 1.0000
10.250 1.3423 0.01919 0.01286 -0.0252 0.0132 1.0000
10.500 1.3394 0.02022 0.01394 -0.0212 0.0108 1.0000
10.750 1.3317 0.02208 0.01588 -0.0183 0.0090 1.0000
11.000 1.3341 0.02422 0.01811 -0.0181 0.0080 1.0000
11.250 1.3366 0.02679 0.02078 -0.0185 0.0078 1.0000
11.500 1.3384 0.02950 0.02356 -0.0189 0.0074 1.0000
11.750 1.3285 0.03347 0.02763 -0.0192 0.0062 1.0000
12.000 1.3268 0.03642 0.03066 -0.0192 0.0058 1.0000
12.250 1.3231 0.03951 0.03385 -0.0193 0.0061 1.0000
12.500 1.3314 0.04128 0.03564 -0.0193 0.0055 1.0000
12.750 1.3264 0.04449 0.03893 -0.0193 0.0052 1.0000
13.000 1.3230 0.04752 0.04203 -0.0193 0.0050 1.0000
13.250 1.3149 0.05106 0.04563 -0.0194 0.0044 1.0000
13.500 1.3120 0.05409 0.04875 -0.0194 0.0045 1.0000
13.750 1.3116 0.05697 0.05168 -0.0196 0.0045 1.0000
14.000 1.2932 0.06212 0.05697 -0.0201 0.0042 1.0000
14.250 1.2875 0.06584 0.06077 -0.0206 0.0040 1.0000
14.500 1.2908 0.06845 0.06344 -0.0209 0.0038 1.0000
14.750 1.2948 0.07099 0.06603 -0.0213 0.0039 1.0000
15.000 1.2867 0.07514 0.07027 -0.0219 0.0040 1.0000
15.250 1.2796 0.07930 0.07452 -0.0226 0.0039 1.0000
15.500 1.2874 0.08142 0.07667 -0.0230 0.0036 1.0000
15.750 1.2763 0.08616 0.08152 -0.0238 0.0037 1.0000
16.000 1.2789 0.08907 0.08449 -0.0244 0.0036 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 77-W-121 (fx77w121-il)