FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 77-W-270 (fx77w270-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.36 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w270-il-1000000.txt Download as CSV file: xf-fx77w270-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-270
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
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2349 0.09006 0.08462 -0.0179 0.7097 0.0065
-19.500 -1.2386 0.08594 0.08025 -0.0194 0.6612 0.0065
-19.250 -1.2408 0.08211 0.07620 -0.0207 0.6231 0.0065
-19.000 -1.2425 0.07838 0.07229 -0.0219 0.5900 0.0066
-18.750 -1.2419 0.07502 0.06878 -0.0228 0.5719 0.0066
-18.500 -1.2407 0.07180 0.06543 -0.0235 0.5590 0.0066
-18.250 -1.2392 0.06870 0.06221 -0.0241 0.5432 0.0066
-18.000 -1.2350 0.06599 0.05939 -0.0246 0.5296 0.0067
-17.750 -1.2313 0.06326 0.05654 -0.0249 0.5187 0.0067
-17.500 -1.2249 0.06089 0.05407 -0.0251 0.5117 0.0067
-17.250 -1.2200 0.05840 0.05148 -0.0253 0.5052 0.0068
-17.000 -1.2124 0.05627 0.04927 -0.0253 0.4991 0.0068
-16.750 -1.2056 0.05409 0.04703 -0.0253 0.4958 0.0069
-16.500 -1.1973 0.05213 0.04499 -0.0251 0.4917 0.0069
-16.250 -1.1884 0.05024 0.04303 -0.0249 0.4875 0.0069
-16.000 -1.1796 0.04838 0.04110 -0.0247 0.4832 0.0070
-15.750 -1.1689 0.04677 0.03941 -0.0244 0.4791 0.0070
-15.500 -1.1583 0.04519 0.03779 -0.0240 0.4772 0.0071
-15.250 -1.1491 0.04355 0.03610 -0.0235 0.4751 0.0071
-15.000 -1.1379 0.04212 0.03462 -0.0230 0.4728 0.0072
-14.750 -1.1255 0.04079 0.03325 -0.0225 0.4704 0.0073
-14.500 -1.1136 0.03944 0.03185 -0.0220 0.4680 0.0074
-14.250 -1.1015 0.03812 0.03048 -0.0214 0.4655 0.0075
-14.000 -1.0879 0.03693 0.02924 -0.0209 0.4626 0.0076
-13.750 -1.0744 0.03573 0.02800 -0.0204 0.4597 0.0078
-13.500 -1.0612 0.03450 0.02674 -0.0198 0.4585 0.0080
-13.250 -1.0466 0.03340 0.02564 -0.0192 0.4575 0.0083
-13.000 -1.0323 0.03229 0.02454 -0.0186 0.4563 0.0085
-12.750 -1.0187 0.03113 0.02338 -0.0179 0.4551 0.0087
-12.500 -1.0045 0.03001 0.02227 -0.0172 0.4537 0.0089
-12.250 -0.9891 0.02898 0.02122 -0.0166 0.4523 0.0121
-12.000 -0.9735 0.02799 0.02019 -0.0160 0.4509 0.0127
-11.750 -0.9583 0.02701 0.01917 -0.0152 0.4494 0.0130
-11.500 -0.9482 0.02595 0.01808 -0.0136 0.4480 0.0132
-11.250 -0.9355 0.02503 0.01711 -0.0125 0.4464 0.0134
-11.000 -0.9140 0.02428 0.01633 -0.0128 0.4445 0.0136
-10.750 -0.8898 0.02363 0.01564 -0.0134 0.4423 0.0138
-10.500 -0.8642 0.02301 0.01499 -0.0143 0.4399 0.0140
-10.250 -0.8373 0.02238 0.01435 -0.0153 0.4387 0.0142
-10.000 -0.8094 0.02184 0.01380 -0.0163 0.4382 0.0145
-9.750 -0.7810 0.02140 0.01334 -0.0171 0.4374 0.0148
-9.500 -0.7522 0.02100 0.01294 -0.0179 0.4365 0.0151
-9.250 -0.7228 0.02062 0.01255 -0.0188 0.4355 0.0153
-9.000 -0.6930 0.02028 0.01220 -0.0197 0.4343 0.0156
-8.750 -0.6628 0.01996 0.01187 -0.0207 0.4333 0.0158
-8.500 -0.6322 0.01969 0.01158 -0.0216 0.4323 0.0161
-8.250 -0.6014 0.01941 0.01130 -0.0226 0.4313 0.0163
-8.000 -0.5704 0.01915 0.01103 -0.0236 0.4303 0.0164
-7.750 -0.5390 0.01891 0.01077 -0.0247 0.4293 0.0166
-7.500 -0.5075 0.01868 0.01053 -0.0257 0.4283 0.0167
-7.250 -0.4759 0.01841 0.01025 -0.0269 0.4272 0.0169
-7.000 -0.4441 0.01815 0.00998 -0.0280 0.4260 0.0171
-6.750 -0.4121 0.01792 0.00974 -0.0292 0.4247 0.0174
-6.500 -0.3799 0.01772 0.00952 -0.0304 0.4235 0.0178
-6.250 -0.3476 0.01755 0.00935 -0.0316 0.4221 0.0182
-6.000 -0.3153 0.01744 0.00922 -0.0328 0.4206 0.0186
-5.750 -0.2830 0.01736 0.00914 -0.0341 0.4192 0.0190
-5.500 -0.2503 0.01719 0.00897 -0.0353 0.4189 0.0194
-5.250 -0.2174 0.01701 0.00880 -0.0365 0.4186 0.0199
-5.000 -0.1845 0.01683 0.00863 -0.0378 0.4182 0.0206
-4.750 -0.1515 0.01667 0.00847 -0.0391 0.4178 0.0213
-4.500 -0.1185 0.01651 0.00834 -0.0404 0.4173 0.0222
-4.250 -0.0854 0.01636 0.00822 -0.0417 0.4168 0.0244
-4.000 -0.0523 0.01623 0.00814 -0.0430 0.4162 0.0323
-3.750 -0.0192 0.01614 0.00807 -0.0443 0.4155 0.0353
-3.500 0.0139 0.01603 0.00797 -0.0456 0.4148 0.0374
-3.250 0.0470 0.01593 0.00788 -0.0468 0.4139 0.0392
-3.000 0.0802 0.01583 0.00779 -0.0482 0.4131 0.0412
-2.750 0.1135 0.01573 0.00769 -0.0495 0.4123 0.0433
-2.500 0.1470 0.01558 0.00761 -0.0509 0.4114 0.0511
-2.250 0.1802 0.01549 0.00755 -0.0523 0.4106 0.0659
-2.000 0.2135 0.01540 0.00747 -0.0536 0.4097 0.0709
-1.750 0.2473 0.01521 0.00738 -0.0552 0.4089 0.0977
-1.500 0.2812 0.01504 0.00730 -0.0568 0.4081 0.1190
-1.250 0.3165 0.01465 0.00715 -0.0589 0.4073 0.1963
-1.000 0.3534 0.01402 0.00693 -0.0618 0.4066 0.3134
-0.750 0.3924 0.01305 0.00660 -0.0654 0.4058 0.4914
-0.500 0.4268 0.01285 0.00664 -0.0672 0.4049 0.5654
-0.250 0.4596 0.01294 0.00681 -0.0684 0.4038 0.5874
0.000 0.4919 0.01314 0.00702 -0.0694 0.4025 0.6018
0.250 0.5240 0.01344 0.00730 -0.0705 0.4008 0.6125
0.500 0.5564 0.01362 0.00744 -0.0716 0.4000 0.6184
0.750 0.5890 0.01365 0.00750 -0.0726 0.3996 0.6228
1.000 0.6215 0.01371 0.00757 -0.0737 0.3991 0.6267
1.250 0.6539 0.01379 0.00767 -0.0747 0.3985 0.6310
1.500 0.6862 0.01389 0.00776 -0.0758 0.3978 0.6349
1.750 0.7187 0.01399 0.00785 -0.0769 0.3970 0.6373
2.000 0.7510 0.01411 0.00796 -0.0779 0.3962 0.6391
2.250 0.7832 0.01412 0.00800 -0.0790 0.3954 0.6434
2.500 0.8152 0.01422 0.00812 -0.0801 0.3946 0.6463
2.750 0.8472 0.01432 0.00823 -0.0811 0.3938 0.6483
3.000 0.8793 0.01440 0.00832 -0.0822 0.3928 0.6502
3.250 0.9113 0.01448 0.00840 -0.0832 0.3918 0.6522
3.500 0.9433 0.01455 0.00847 -0.0843 0.3905 0.6549
3.750 0.9753 0.01463 0.00853 -0.0853 0.3890 0.6574
4.000 1.0072 0.01472 0.00858 -0.0864 0.3866 0.6591
4.250 1.0387 0.01481 0.00865 -0.0875 0.3833 0.6628
4.500 1.0698 0.01495 0.00882 -0.0884 0.3813 0.6662
4.750 1.1015 0.01498 0.00889 -0.0894 0.3805 0.6685
5.000 1.1334 0.01500 0.00893 -0.0905 0.3795 0.6695
5.250 1.1654 0.01501 0.00896 -0.0917 0.3782 0.6704
5.500 1.1973 0.01504 0.00901 -0.0928 0.3767 0.6712
5.750 1.2291 0.01507 0.00905 -0.0940 0.3751 0.6720
6.000 1.2608 0.01512 0.00910 -0.0951 0.3736 0.6727
6.250 1.2924 0.01517 0.00916 -0.0963 0.3719 0.6735
6.500 1.3238 0.01524 0.00922 -0.0974 0.3702 0.6744
6.750 1.3550 0.01533 0.00930 -0.0985 0.3682 0.6753
7.000 1.3859 0.01546 0.00942 -0.0995 0.3660 0.6763
7.250 1.4164 0.01563 0.00959 -0.1005 0.3636 0.6771
7.500 1.4478 0.01569 0.00968 -0.1017 0.3627 0.6779
7.750 1.4790 0.01576 0.00978 -0.1028 0.3615 0.6784
8.000 1.5101 0.01584 0.00989 -0.1039 0.3599 0.6789
8.250 1.5411 0.01592 0.01000 -0.1049 0.3577 0.6794
8.500 1.5718 0.01601 0.01011 -0.1060 0.3553 0.6798
8.750 1.6024 0.01611 0.01022 -0.1070 0.3526 0.6801
9.000 1.6325 0.01624 0.01033 -0.1080 0.3489 0.6805
9.250 1.6623 0.01641 0.01049 -0.1090 0.3455 0.6807
9.500 1.6924 0.01652 0.01062 -0.1100 0.3426 0.6815
9.750 1.7220 0.01666 0.01076 -0.1110 0.3381 0.6824
10.000 1.7500 0.01694 0.01099 -0.1118 0.3306 0.6832
10.250 1.7781 0.01721 0.01125 -0.1125 0.3251 0.6839
10.500 1.8050 0.01757 0.01160 -0.1131 0.3193 0.6846
10.750 1.8306 0.01802 0.01202 -0.1136 0.3138 0.6853
11.000 1.8582 0.01827 0.01232 -0.1142 0.3105 0.6859
11.250 1.8840 0.01866 0.01271 -0.1147 0.3029 0.6865
11.500 1.9050 0.01939 0.01339 -0.1145 0.2903 0.6871
11.750 1.9132 0.02095 0.01479 -0.1126 0.2663 0.6876
12.000 1.9199 0.02238 0.01618 -0.1104 0.2528 0.6880
12.250 1.9183 0.02397 0.01777 -0.1069 0.2438 0.6885
12.500 1.8935 0.02687 0.02076 -0.1009 0.2340 0.6889
12.750 1.8532 0.03319 0.02717 -0.0978 0.2224 0.6891
13.000 1.8140 0.04064 0.03477 -0.0969 0.2166 0.6894
13.250 1.7724 0.04845 0.04276 -0.0959 0.2154 0.6896
13.500 1.7262 0.05640 0.05089 -0.0944 0.2151 0.6897
13.750 1.6795 0.06427 0.05891 -0.0929 0.2148 0.6898
14.000 1.6379 0.07166 0.06642 -0.0917 0.2134 0.6900
14.250 1.6004 0.07890 0.07375 -0.0910 0.2104 0.6901
14.500 1.5713 0.08538 0.08029 -0.0907 0.2068 0.6903
14.750 1.5443 0.09165 0.08659 -0.0905 0.2006 0.6905
|
Polar data table (+)
Polar graphs
<< Back to FX 77-W-270 (fx77w270-il)