FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.32 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w121-il-1000000-n5.txt Download as CSV file: xf-fx77w121-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3062 0.09783 0.09420 -0.0272 0.4509 0.0048
-9.750 -0.2962 0.09593 0.09229 -0.0283 0.4493 0.0056
-8.250 -0.5619 0.02156 0.01648 -0.0402 0.4530 0.0059
-8.000 -0.5428 0.02031 0.01501 -0.0389 0.4511 0.0062
-7.750 -0.5256 0.01870 0.01311 -0.0372 0.4495 0.0063
-7.500 -0.5066 0.01731 0.01147 -0.0356 0.4484 0.0063
-7.250 -0.4819 0.01697 0.01104 -0.0350 0.4472 0.0064
-7.000 -0.4597 0.01610 0.01000 -0.0339 0.4459 0.0065
-6.750 -0.4381 0.01511 0.00880 -0.0327 0.4445 0.0067
-6.500 -0.4153 0.01432 0.00787 -0.0317 0.4432 0.0070
-6.250 -0.3904 0.01393 0.00740 -0.0310 0.4417 0.0073
-6.000 -0.3659 0.01344 0.00681 -0.0303 0.4404 0.0074
-5.750 -0.3410 0.01303 0.00632 -0.0296 0.4392 0.0076
-5.500 -0.3151 0.01279 0.00603 -0.0291 0.4380 0.0080
-5.250 -0.2897 0.01248 0.00563 -0.0285 0.4368 0.0085
-5.000 -0.2642 0.01218 0.00525 -0.0279 0.4356 0.0088
-4.750 -0.2386 0.01187 0.00488 -0.0273 0.4346 0.0092
-4.500 -0.2129 0.01156 0.00450 -0.0267 0.4340 0.0093
-4.250 -0.1876 0.01119 0.00407 -0.0260 0.4332 0.0101
-4.000 -0.1614 0.01098 0.00386 -0.0256 0.4324 0.0109
-3.750 -0.1353 0.01076 0.00359 -0.0251 0.4315 0.0113
-3.500 -0.1089 0.01058 0.00338 -0.0246 0.4307 0.0122
-3.250 -0.0823 0.01044 0.00320 -0.0242 0.4299 0.0129
-3.000 -0.0563 0.01021 0.00295 -0.0237 0.4292 0.0139
-2.750 -0.0296 0.01009 0.00282 -0.0233 0.4283 0.0154
-2.500 -0.0030 0.00997 0.00269 -0.0230 0.4274 0.0166
-2.250 0.0237 0.00986 0.00255 -0.0226 0.4264 0.0176
-2.000 0.0501 0.00971 0.00238 -0.0222 0.4255 0.0194
-1.750 0.0767 0.00960 0.00226 -0.0218 0.4246 0.0212
-1.500 0.1036 0.00953 0.00218 -0.0215 0.4238 0.0231
-1.250 0.1305 0.00947 0.00209 -0.0212 0.4230 0.0242
-1.000 0.1570 0.00936 0.00196 -0.0208 0.4221 0.0271
-0.750 0.1836 0.00929 0.00189 -0.0205 0.4213 0.0301
-0.500 0.2104 0.00926 0.00183 -0.0202 0.4203 0.0329
-0.250 0.2372 0.00919 0.00178 -0.0199 0.4197 0.0386
0.000 0.2640 0.00910 0.00173 -0.0196 0.4191 0.0511
0.250 0.2905 0.00898 0.00169 -0.0192 0.4185 0.0795
0.500 0.3165 0.00881 0.00167 -0.0188 0.4178 0.1297
0.750 0.3418 0.00861 0.00166 -0.0183 0.4172 0.2015
1.000 0.3657 0.00829 0.00167 -0.0176 0.4165 0.3228
1.250 0.3877 0.00787 0.00169 -0.0165 0.4159 0.4823
1.500 0.3990 0.00704 0.00168 -0.0131 0.4152 0.7503
2.000 0.5962 0.00713 0.00223 -0.0442 0.4120 0.9914
2.250 0.6383 0.00719 0.00225 -0.0473 0.4105 0.9944
2.500 0.6725 0.00725 0.00229 -0.0488 0.4095 0.9962
2.750 0.7064 0.00728 0.00229 -0.0502 0.4082 0.9975
3.000 0.7361 0.00734 0.00232 -0.0507 0.4061 0.9982
3.250 0.7658 0.00738 0.00235 -0.0511 0.4047 0.9988
3.500 0.7956 0.00739 0.00238 -0.0516 0.4034 0.9994
3.750 0.8254 0.00739 0.00239 -0.0521 0.4012 0.9998
4.000 0.8532 0.00741 0.00242 -0.0522 0.3994 1.0000
4.250 0.8791 0.00745 0.00247 -0.0519 0.3976 1.0000
4.500 0.9049 0.00749 0.00252 -0.0515 0.3954 1.0000
4.750 0.9306 0.00754 0.00258 -0.0511 0.3937 1.0000
5.000 0.9561 0.00761 0.00265 -0.0508 0.3921 1.0000
5.250 0.9817 0.00769 0.00274 -0.0504 0.3905 1.0000
5.500 1.0076 0.00773 0.00283 -0.0501 0.3892 1.0000
5.750 1.0335 0.00778 0.00292 -0.0498 0.3874 1.0000
6.000 1.0595 0.00782 0.00300 -0.0495 0.3844 1.0000
6.250 1.0852 0.00788 0.00310 -0.0492 0.3818 1.0000
6.500 1.1108 0.00795 0.00319 -0.0489 0.3792 1.0000
6.750 1.1363 0.00803 0.00329 -0.0485 0.3765 1.0000
7.000 1.1621 0.00808 0.00340 -0.0483 0.3712 1.0000
7.250 1.1873 0.00817 0.00349 -0.0479 0.3626 1.0000
7.500 1.2109 0.00839 0.00362 -0.0473 0.3395 1.0000
7.750 1.2321 0.00884 0.00394 -0.0465 0.3093 1.0000
8.000 1.2458 0.00999 0.00474 -0.0446 0.2471 1.0000
8.250 1.2620 0.01088 0.00542 -0.0432 0.2089 1.0000
8.500 1.2772 0.01180 0.00615 -0.0416 0.1714 1.0000
8.750 1.2907 0.01281 0.00696 -0.0397 0.1339 1.0000
9.000 1.2965 0.01432 0.00818 -0.0370 0.0834 1.0000
9.250 1.3006 0.01581 0.00945 -0.0339 0.0442 1.0000
9.500 1.3042 0.01717 0.01067 -0.0309 0.0184 1.0000
9.750 1.3150 0.01798 0.01149 -0.0287 0.0123 1.0000
10.000 1.3252 0.01880 0.01233 -0.0266 0.0095 1.0000
10.250 1.3323 0.01963 0.01321 -0.0240 0.0075 1.0000
10.500 1.3303 0.02062 0.01425 -0.0203 0.0064 1.0000
10.750 1.3312 0.02208 0.01578 -0.0184 0.0060 1.0000
11.000 1.3342 0.02416 0.01794 -0.0182 0.0052 1.0000
11.250 1.3393 0.02642 0.02028 -0.0185 0.0051 1.0000
11.500 1.3433 0.02888 0.02281 -0.0189 0.0049 1.0000
11.750 1.3417 0.03192 0.02591 -0.0192 0.0041 1.0000
12.000 1.3423 0.03464 0.02871 -0.0194 0.0037 1.0000
12.250 1.3434 0.03725 0.03139 -0.0194 0.0038 1.0000
12.500 1.3459 0.03965 0.03384 -0.0195 0.0034 1.0000
12.750 1.3428 0.04266 0.03692 -0.0195 0.0032 1.0000
13.000 1.3402 0.04559 0.03991 -0.0194 0.0030 1.0000
13.250 1.3366 0.04862 0.04301 -0.0195 0.0026 1.0000
13.500 1.3366 0.05128 0.04574 -0.0195 0.0028 1.0000
13.750 1.3350 0.05416 0.04868 -0.0196 0.0026 1.0000
14.000 1.3274 0.05789 0.05250 -0.0199 0.0025 1.0000
14.250 1.3300 0.06045 0.05512 -0.0201 0.0024 1.0000
14.500 1.3309 0.06330 0.05803 -0.0204 0.0022 1.0000
14.750 1.3350 0.06577 0.06054 -0.0208 0.0023 1.0000
15.000 1.3331 0.06899 0.06383 -0.0211 0.0023 1.0000
15.250 1.3296 0.07251 0.06745 -0.0217 0.0023 1.0000
15.500 1.3340 0.07502 0.07000 -0.0220 0.0020 1.0000
15.750 1.3292 0.07880 0.07386 -0.0227 0.0021 1.0000
16.000 1.3305 0.08175 0.07687 -0.0232 0.0020 1.0000
16.250 1.3282 0.08526 0.08046 -0.0239 0.0019 1.0000
16.500 1.3283 0.08847 0.08374 -0.0246 0.0018 1.0000
16.750 1.3248 0.09225 0.08760 -0.0254 0.0018 1.0000
17.000 1.3241 0.09562 0.09103 -0.0262 0.0018 1.0000
17.250 1.3222 0.09923 0.09470 -0.0271 0.0016 1.0000
17.500 1.3182 0.10319 0.09874 -0.0281 0.0016 1.0000
17.750 1.3159 0.10696 0.10258 -0.0292 0.0016 1.0000
18.000 1.3108 0.11120 0.10690 -0.0304 0.0016 1.0000
18.250 1.3098 0.11481 0.11059 -0.0315 0.0017 1.0000
18.500 1.3014 0.11963 0.11548 -0.0331 0.0014 1.0000
18.750 1.3007 0.12328 0.11921 -0.0343 0.0015 1.0000
19.000 1.2960 0.12764 0.12366 -0.0358 0.0016 1.0000
19.250 1.2836 0.13339 0.12951 -0.0380 0.0015 1.0000
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