FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: FX 63-158 AIRFOIL (fx63158-il) Reynolds number: 100,000 Max Cl/Cd: 51.43 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63158-il-100000-n5.txt Download as CSV file: xf-fx63158-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-158 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3008 0.11909 0.11421 -0.0469 1.0000 0.0508
-10.750 -0.3021 0.11554 0.11073 -0.0479 1.0000 0.0515
-10.500 -0.3277 0.10960 0.10494 -0.0538 1.0000 0.0536
-10.250 -0.3186 0.10695 0.10233 -0.0519 1.0000 0.0542
-10.000 -0.3174 0.10393 0.09938 -0.0516 1.0000 0.0545
-9.750 -0.3188 0.10081 0.09633 -0.0515 1.0000 0.0549
-9.500 -0.3386 0.08933 0.08486 -0.0567 1.0000 0.0300
-9.000 -0.3393 0.07649 0.07203 -0.0670 0.9907 0.0252
-8.750 -0.3366 0.07075 0.06622 -0.0734 0.9781 0.0245
-8.500 -0.3434 0.06508 0.06044 -0.0789 0.9589 0.0238
-8.250 -0.3683 0.05746 0.05239 -0.0850 0.9300 0.0219
-8.000 -0.3568 0.05355 0.04825 -0.0880 0.9141 0.0213
-7.750 -0.3419 0.04954 0.04396 -0.0911 0.8995 0.0208
-7.500 -0.3220 0.04525 0.03927 -0.0946 0.8867 0.0203
-7.250 -0.2954 0.04112 0.03465 -0.0982 0.8752 0.0198
-7.000 -0.2689 0.03769 0.03073 -0.1006 0.8602 0.0194
-6.750 -0.2384 0.03459 0.02709 -0.1029 0.8462 0.0191
-6.500 -0.2043 0.03205 0.02412 -0.1052 0.8331 0.0194
-6.250 -0.1686 0.02997 0.02157 -0.1075 0.8201 0.0206
-6.000 -0.1343 0.02816 0.01926 -0.1090 0.8059 0.0219
-5.750 -0.1027 0.02667 0.01764 -0.1100 0.7914 0.0227
-5.500 -0.0720 0.02534 0.01610 -0.1103 0.7775 0.0231
-5.250 -0.0424 0.02422 0.01482 -0.1104 0.7647 0.0235
-5.000 -0.0136 0.02325 0.01371 -0.1103 0.7531 0.0240
-4.750 0.0119 0.02245 0.01284 -0.1098 0.7417 0.0246
-4.500 0.0387 0.02172 0.01199 -0.1096 0.7320 0.0254
-4.250 0.0642 0.02108 0.01128 -0.1096 0.7221 0.0265
-4.000 0.0906 0.02053 0.01060 -0.1098 0.7130 0.0281
-3.750 0.1175 0.02007 0.00998 -0.1099 0.7041 0.0305
-3.500 0.1449 0.01964 0.00938 -0.1101 0.6963 0.0356
-3.250 0.1715 0.01897 0.00867 -0.1104 0.6888 0.0487
-3.000 0.1891 0.01710 0.00932 -0.1099 0.6831 0.5261
-2.750 0.2144 0.01784 0.00999 -0.1084 0.6761 0.6078
-2.500 0.2439 0.01844 0.01035 -0.1083 0.6701 0.6424
-2.250 0.2711 0.01890 0.01062 -0.1076 0.6650 0.6587
-2.000 0.2956 0.01934 0.01093 -0.1065 0.6588 0.6739
-1.750 0.3230 0.01967 0.01110 -0.1062 0.6533 0.6879
-1.250 0.3723 0.02017 0.01138 -0.1043 0.6425 0.7046
-1.000 0.3922 0.02043 0.01160 -0.1020 0.6371 0.7106
-0.750 0.4194 0.02062 0.01164 -0.1018 0.6325 0.7198
-0.500 0.4416 0.02078 0.01177 -0.1005 0.6271 0.7265
-0.250 0.4651 0.02091 0.01183 -0.0995 0.6216 0.7325
0.000 0.4977 0.02094 0.01172 -0.1011 0.6168 0.7390
0.250 0.5219 0.02100 0.01172 -0.1004 0.6120 0.7424
0.500 0.5455 0.02106 0.01177 -0.0996 0.6061 0.7456
0.750 0.5731 0.02108 0.01169 -0.0998 0.6002 0.7490
1.000 0.6016 0.02111 0.01164 -0.1004 0.5933 0.7530
1.250 0.6304 0.02110 0.01157 -0.1012 0.5849 0.7568
1.500 0.6545 0.02110 0.01150 -0.1004 0.5782 0.7594
1.750 0.6766 0.02111 0.01154 -0.0994 0.5697 0.7623
2.000 0.7042 0.02108 0.01140 -0.0995 0.5627 0.7650
2.250 0.7294 0.02111 0.01147 -0.0995 0.5544 0.7675
2.500 0.7588 0.02111 0.01140 -0.1002 0.5477 0.7699
2.750 0.7878 0.02120 0.01147 -0.1010 0.5411 0.7727
3.000 0.8128 0.02128 0.01159 -0.1008 0.5353 0.7753
3.250 0.8377 0.02135 0.01168 -0.1003 0.5306 0.7780
3.500 0.8628 0.02146 0.01183 -0.1001 0.5255 0.7807
3.750 0.8881 0.02160 0.01204 -0.1001 0.5195 0.7830
4.000 0.9158 0.02171 0.01217 -0.1005 0.5142 0.7848
4.250 0.9436 0.02184 0.01236 -0.1010 0.5091 0.7867
4.500 0.9703 0.02202 0.01264 -0.1014 0.5029 0.7886
4.750 0.9992 0.02217 0.01283 -0.1021 0.4978 0.7904
5.000 1.0262 0.02232 0.01303 -0.1024 0.4937 0.7921
5.250 1.0489 0.02254 0.01340 -0.1018 0.4886 0.7940
5.500 1.0733 0.02273 0.01370 -0.1015 0.4837 0.7960
5.750 1.0996 0.02287 0.01389 -0.1016 0.4790 0.7979
6.000 1.1230 0.02311 0.01427 -0.1013 0.4720 0.7997
6.250 1.1471 0.02330 0.01456 -0.1011 0.4642 0.8016
6.500 1.1707 0.02353 0.01490 -0.1008 0.4558 0.8035
6.750 1.1936 0.02379 0.01529 -0.1005 0.4465 0.8054
7.000 1.2165 0.02408 0.01572 -0.1003 0.4372 0.8073
7.250 1.2383 0.02429 0.01603 -0.0996 0.4285 0.8091
7.500 1.2571 0.02459 0.01647 -0.0984 0.4199 0.8110
7.750 1.2775 0.02484 0.01680 -0.0975 0.4127 0.8133
8.000 1.2956 0.02525 0.01738 -0.0963 0.4042 0.8157
8.250 1.3133 0.02562 0.01786 -0.0951 0.3951 0.8182
8.500 1.3273 0.02618 0.01861 -0.0934 0.3838 0.8206
8.750 1.3419 0.02674 0.01930 -0.0920 0.3713 0.8229
9.000 1.3557 0.02733 0.01995 -0.0904 0.3580 0.8255
9.250 1.3648 0.02797 0.02059 -0.0879 0.3452 0.8280
9.500 1.3714 0.02889 0.02161 -0.0855 0.3293 0.8307
9.750 1.3758 0.03006 0.02287 -0.0832 0.3076 0.8336
10.000 1.3763 0.03150 0.02425 -0.0806 0.2903 0.8363
10.250 1.3775 0.03316 0.02594 -0.0786 0.2743 0.8389
10.500 1.3797 0.03502 0.02792 -0.0772 0.2526 0.8416
10.750 1.3713 0.03759 0.03041 -0.0751 0.2365 0.8442
11.000 1.3626 0.04044 0.03322 -0.0734 0.2244 0.8468
11.250 1.3634 0.04283 0.03581 -0.0726 0.2053 0.8498
11.500 1.3538 0.04630 0.03925 -0.0718 0.1874 0.8530
11.750 1.3448 0.04995 0.04287 -0.0713 0.1774 0.8562
12.000 1.3412 0.05324 0.04626 -0.0712 0.1663 0.8595
12.250 1.3397 0.05624 0.04942 -0.0709 0.1465 0.8627
12.500 1.3272 0.06057 0.05368 -0.0709 0.1369 0.8657
12.750 1.3182 0.06470 0.05779 -0.0711 0.1296 0.8688
13.000 1.3153 0.06827 0.06147 -0.0714 0.1206 0.8722
13.500 1.3103 0.07553 0.06892 -0.0724 0.0994 0.8795
13.750 1.3038 0.07973 0.07311 -0.0730 0.0944 0.8834
14.000 1.2977 0.08399 0.07736 -0.0738 0.0902 0.8877
14.500 1.2947 0.09114 0.08471 -0.0749 0.0810 0.8991
14.750 1.2973 0.09416 0.08796 -0.0754 0.0753 0.9079
15.000 1.2979 0.09729 0.09125 -0.0758 0.0705 0.9216
15.250 1.2964 0.10060 0.09469 -0.0765 0.0669 0.9639
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