FX 83-W-160 (fx83w160-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 83-W-160 (fx83w160-il) Reynolds number: 200,000 Max Cl/Cd: 76.48 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx83w160-il-200000.txt Download as CSV file: xf-fx83w160-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-160
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6635 0.08760 0.08357 -0.0775 1.0000 0.0496
-13.750 -0.7034 0.08007 0.07598 -0.0797 1.0000 0.0491
-13.500 -0.7459 0.07343 0.06924 -0.0815 1.0000 0.0487
-13.250 -0.7867 0.06793 0.06362 -0.0823 1.0000 0.0485
-13.000 -0.8195 0.06228 0.05777 -0.0850 0.9987 0.0484
-12.750 -0.8390 0.05574 0.05089 -0.0918 0.9940 0.0485
-12.500 -0.8538 0.05090 0.04571 -0.0966 0.9877 0.0488
-12.250 -0.8703 0.04759 0.04205 -0.0987 0.9794 0.0493
-12.000 -0.8727 0.04450 0.03862 -0.0999 0.9730 0.0500
-11.750 -0.8547 0.04263 0.03676 -0.1006 0.9688 0.0511
-11.500 -0.8322 0.04108 0.03512 -0.1025 0.9657 0.0525
-11.250 -0.8225 0.03960 0.03350 -0.1018 0.9596 0.0536
-11.000 -0.8048 0.03771 0.03134 -0.1028 0.9550 0.0552
-10.750 -0.7803 0.03572 0.02893 -0.1051 0.9521 0.0572
-10.500 -0.7709 0.03449 0.02777 -0.1029 0.9456 0.0585
-10.250 -0.7466 0.03348 0.02673 -0.1036 0.9420 0.0605
-10.000 -0.7182 0.03223 0.02530 -0.1051 0.9395 0.0630
-9.500 -0.6820 0.03008 0.02296 -0.1039 0.9297 0.0676
-9.250 -0.6541 0.02932 0.02216 -0.1048 0.9266 0.0709
-9.000 -0.6228 0.02848 0.02107 -0.1064 0.9244 0.0746
-8.750 -0.5902 0.02730 0.02001 -0.1082 0.9230 0.0789
-8.500 -0.5858 0.02701 0.01966 -0.1046 0.9149 0.0818
-8.250 -0.5585 0.02617 0.01872 -0.1052 0.9115 0.0865
-8.000 -0.5267 0.02549 0.01809 -0.1067 0.9093 0.0920
-7.750 -0.4928 0.02474 0.01724 -0.1084 0.9078 0.0985
-7.500 -0.4836 0.02450 0.01704 -0.1057 0.9014 0.1028
-7.250 -0.4609 0.02423 0.01664 -0.1052 0.8969 0.1094
-7.000 -0.4313 0.02347 0.01599 -0.1062 0.8943 0.1176
-6.750 -0.3971 0.02281 0.01531 -0.1079 0.8925 0.1274
-6.500 -0.3603 0.02237 0.01479 -0.1100 0.8912 0.1383
-6.250 -0.3586 0.02228 0.01481 -0.1059 0.8833 0.1445
-6.000 -0.3333 0.02196 0.01445 -0.1058 0.8797 0.1557
-5.750 -0.3017 0.02148 0.01399 -0.1070 0.8775 0.1695
-5.500 -0.2670 0.02089 0.01347 -0.1087 0.8758 0.1871
-5.250 -0.2308 0.02022 0.01295 -0.1108 0.8746 0.2095
-5.000 -0.2287 0.02044 0.01323 -0.1067 0.8664 0.2251
-4.750 -0.2025 0.02002 0.01297 -0.1069 0.8628 0.2586
-4.500 -0.1704 0.01946 0.01266 -0.1082 0.8606 0.3111
-4.250 -0.1363 0.01899 0.01245 -0.1097 0.8591 0.3722
-4.000 -0.0998 0.01874 0.01235 -0.1114 0.8579 0.4227
-3.750 -0.0984 0.01939 0.01303 -0.1069 0.8493 0.4463
-3.500 -0.0722 0.01954 0.01323 -0.1065 0.8457 0.4722
-3.250 -0.0396 0.01963 0.01331 -0.1073 0.8436 0.4948
-3.000 -0.0043 0.01970 0.01332 -0.1085 0.8421 0.5149
-2.750 0.0325 0.01974 0.01332 -0.1099 0.8410 0.5323
-2.500 0.0285 0.02072 0.01433 -0.1046 0.8319 0.5406
-2.250 0.0558 0.02091 0.01447 -0.1044 0.8284 0.5543
-2.000 0.0891 0.02093 0.01451 -0.1052 0.8264 0.5658
-1.750 0.1243 0.02088 0.01445 -0.1063 0.8250 0.5765
-1.500 0.1617 0.02081 0.01431 -0.1079 0.8240 0.5886
-1.250 0.1517 0.02202 0.01559 -0.1017 0.8138 0.5939
-1.000 0.1808 0.02212 0.01567 -0.1019 0.8107 0.6049
-0.750 0.2161 0.02198 0.01556 -0.1028 0.8089 0.6147
-0.500 0.2552 0.02173 0.01528 -0.1046 0.8077 0.6267
-0.250 0.2944 0.02143 0.01504 -0.1062 0.8068 0.6358
0.000 0.2814 0.02283 0.01641 -0.0998 0.7952 0.6425
0.250 0.3121 0.02277 0.01640 -0.1001 0.7929 0.6497
0.500 0.3486 0.02254 0.01617 -0.1015 0.7914 0.6570
0.750 0.3882 0.02217 0.01579 -0.1034 0.7904 0.6641
1.000 0.4273 0.02183 0.01549 -0.1052 0.7895 0.6709
1.250 0.4687 0.02152 0.01516 -0.1075 0.7887 0.6786
1.500 0.5090 0.02118 0.01486 -0.1096 0.7872 0.6839
1.750 0.4933 0.02231 0.01603 -0.1023 0.7743 0.6887
2.000 0.5356 0.02185 0.01557 -0.1046 0.7733 0.6956
2.250 0.5803 0.02128 0.01504 -0.1074 0.7723 0.7014
2.500 0.6301 0.02063 0.01444 -0.1110 0.7715 0.7082
2.750 0.6824 0.02002 0.01383 -0.1152 0.7701 0.7159
3.000 0.6624 0.02089 0.01478 -0.1065 0.7574 0.7207
3.250 0.7216 0.01981 0.01375 -0.1116 0.7563 0.7272
3.500 0.8056 0.01793 0.01184 -0.1208 0.7542 0.7340
3.750 0.8063 0.01809 0.01209 -0.1155 0.7430 0.7391
4.000 0.8620 0.01713 0.01116 -0.1200 0.7388 0.7461
4.250 0.8840 0.01701 0.01108 -0.1186 0.7310 0.7530
4.500 0.9137 0.01668 0.01083 -0.1186 0.7240 0.7594
4.750 0.9647 0.01607 0.01023 -0.1226 0.7193 0.7676
5.000 0.9669 0.01622 0.01050 -0.1174 0.7086 0.7750
5.250 1.0083 0.01567 0.00998 -0.1195 0.7007 0.7841
5.500 1.0208 0.01554 0.00994 -0.1161 0.6891 0.7932
5.750 1.0370 0.01538 0.00984 -0.1135 0.6778 0.8041
6.000 1.0638 0.01504 0.00956 -0.1128 0.6662 0.8152
6.250 1.0761 0.01489 0.00951 -0.1094 0.6527 0.8296
6.500 1.0852 0.01486 0.00957 -0.1054 0.6370 0.8495
6.750 1.0987 0.01475 0.00956 -0.1023 0.6193 0.8813
7.000 1.1205 0.01465 0.00958 -0.1012 0.5959 1.0000
7.250 1.1348 0.01488 0.00967 -0.0988 0.5653 1.0000
7.500 1.1432 0.01532 0.00989 -0.0953 0.5245 1.0000
7.750 1.1445 0.01607 0.01030 -0.0907 0.4733 1.0000
8.000 1.1401 0.01716 0.01105 -0.0855 0.4223 1.0000
8.250 1.1341 0.01847 0.01204 -0.0804 0.3759 1.0000
8.500 1.1293 0.01987 0.01317 -0.0759 0.3339 1.0000
8.750 1.1272 0.02130 0.01436 -0.0719 0.2976 1.0000
9.000 1.1280 0.02271 0.01556 -0.0686 0.2680 1.0000
9.250 1.1311 0.02408 0.01676 -0.0657 0.2439 1.0000
9.750 1.1438 0.02666 0.01909 -0.0610 0.2091 1.0000
10.000 1.1535 0.02781 0.02019 -0.0592 0.1951 1.0000
10.250 1.1637 0.02897 0.02131 -0.0574 0.1827 1.0000
10.500 1.1737 0.03019 0.02246 -0.0557 0.1724 1.0000
10.750 1.1838 0.03140 0.02361 -0.0541 0.1625 1.0000
11.000 1.1958 0.03252 0.02476 -0.0527 0.1533 1.0000
11.250 1.2052 0.03387 0.02598 -0.0511 0.1449 1.0000
11.500 1.2180 0.03494 0.02716 -0.0499 0.1370 1.0000
11.750 1.2280 0.03631 0.02841 -0.0485 0.1299 1.0000
12.000 1.2403 0.03745 0.02967 -0.0473 0.1232 1.0000
12.250 1.2504 0.03885 0.03098 -0.0460 0.1171 1.0000
12.500 1.2625 0.04008 0.03231 -0.0449 0.1114 1.0000
12.750 1.2725 0.04148 0.03370 -0.0437 0.1060 1.0000
13.000 1.2844 0.04286 0.03508 -0.0426 0.1011 1.0000
13.250 1.2948 0.04425 0.03657 -0.0416 0.0963 1.0000
13.500 1.3048 0.04574 0.03800 -0.0406 0.0921 1.0000
13.750 1.3157 0.04723 0.03958 -0.0396 0.0881 1.0000
14.000 1.3252 0.04878 0.04120 -0.0386 0.0842 1.0000
14.250 1.3357 0.05033 0.04270 -0.0377 0.0808 1.0000
14.500 1.3457 0.05199 0.04447 -0.0368 0.0775 1.0000
14.750 1.3538 0.05373 0.04631 -0.0360 0.0744 1.0000
15.000 1.3620 0.05548 0.04804 -0.0352 0.0715 1.0000
15.250 1.3736 0.05716 0.04976 -0.0345 0.0687 1.0000
15.500 1.3790 0.05925 0.05202 -0.0337 0.0663 1.0000
15.750 1.3858 0.06122 0.05406 -0.0331 0.0640 1.0000
16.000 1.3958 0.06295 0.05574 -0.0325 0.0618 1.0000
16.250 1.4032 0.06510 0.05801 -0.0319 0.0597 1.0000
16.500 1.4050 0.06770 0.06080 -0.0314 0.0579 1.0000
16.750 1.4084 0.07014 0.06335 -0.0310 0.0562 1.0000
17.000 1.4148 0.07229 0.06552 -0.0308 0.0546 1.0000
17.250 1.4271 0.07405 0.06724 -0.0304 0.0527 1.0000
17.500 1.4217 0.07756 0.07100 -0.0303 0.0516 1.0000
17.750 1.4189 0.08092 0.07457 -0.0304 0.0505 1.0000
18.000 1.4167 0.08424 0.07805 -0.0307 0.0492 1.0000
18.250 1.4175 0.08721 0.08110 -0.0310 0.0480 1.0000
18.500 1.4246 0.08937 0.08323 -0.0311 0.0467 1.0000
18.750 1.4275 0.09235 0.08628 -0.0314 0.0456 1.0000
19.000 1.4139 0.09741 0.09162 -0.0326 0.0450 1.0000
19.250 1.4017 0.10248 0.09695 -0.0342 0.0443 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 83-W-160 (fx83w160-il)