FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL1-152 (fx73cl1152-il) Reynolds number: 500,000 Max Cl/Cd: 106.51 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl1152-il-500000-n5.txt Download as CSV file: xf-fx73cl1152-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL1-152
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1401 0.10763 0.10296 -0.0651 0.5276 0.0239
-11.250 -0.5578 0.03045 0.02547 -0.1192 0.5965 0.0285
-11.000 -0.5459 0.02841 0.02322 -0.1202 0.5835 0.0288
-10.500 -0.5132 0.02541 0.01983 -0.1208 0.5594 0.0294
-10.250 -0.4942 0.02417 0.01838 -0.1207 0.5492 0.0297
-10.000 -0.4736 0.02305 0.01707 -0.1206 0.5393 0.0301
-9.750 -0.4521 0.02205 0.01586 -0.1204 0.5304 0.0304
-9.500 -0.4294 0.02114 0.01477 -0.1202 0.5219 0.0307
-9.250 -0.4061 0.02036 0.01378 -0.1199 0.5136 0.0310
-9.000 -0.3822 0.01960 0.01291 -0.1196 0.5066 0.0314
-8.750 -0.3575 0.01902 0.01225 -0.1193 0.4989 0.0317
-8.500 -0.3323 0.01854 0.01167 -0.1190 0.4921 0.0321
-8.250 -0.3065 0.01810 0.01115 -0.1187 0.4855 0.0325
-8.000 -0.2805 0.01769 0.01065 -0.1184 0.4789 0.0329
-7.750 -0.2545 0.01729 0.01014 -0.1180 0.4735 0.0335
-7.500 -0.2280 0.01687 0.00962 -0.1178 0.4688 0.0341
-7.250 -0.2015 0.01645 0.00909 -0.1174 0.4640 0.0346
-7.000 -0.1750 0.01607 0.00857 -0.1171 0.4593 0.0351
-6.750 -0.1485 0.01567 0.00808 -0.1168 0.4553 0.0355
-6.500 -0.1216 0.01529 0.00767 -0.1165 0.4518 0.0361
-6.250 -0.0944 0.01500 0.00733 -0.1162 0.4481 0.0366
-6.000 -0.0672 0.01473 0.00700 -0.1159 0.4442 0.0372
-5.750 -0.0400 0.01449 0.00668 -0.1156 0.4403 0.0379
-5.500 -0.0127 0.01427 0.00638 -0.1152 0.4368 0.0387
-5.250 0.0150 0.01403 0.00608 -0.1150 0.4341 0.0395
-5.000 0.0426 0.01376 0.00577 -0.1147 0.4313 0.0403
-4.750 0.0701 0.01353 0.00552 -0.1144 0.4285 0.0411
-4.500 0.0978 0.01335 0.00530 -0.1141 0.4257 0.0420
-4.250 0.1254 0.01319 0.00508 -0.1138 0.4231 0.0429
-4.000 0.1530 0.01305 0.00487 -0.1135 0.4205 0.0439
-3.750 0.1809 0.01289 0.00467 -0.1132 0.4183 0.0449
-3.500 0.2088 0.01271 0.00450 -0.1130 0.4161 0.0462
-3.250 0.2368 0.01259 0.00435 -0.1127 0.4136 0.0477
-3.000 0.2648 0.01248 0.00421 -0.1125 0.4112 0.0493
-2.750 0.2927 0.01236 0.00406 -0.1122 0.4090 0.0507
-2.500 0.3205 0.01225 0.00395 -0.1119 0.4069 0.0525
-2.250 0.3484 0.01219 0.00385 -0.1116 0.4048 0.0546
-2.000 0.3761 0.01214 0.00376 -0.1113 0.4025 0.0569
-1.750 0.4040 0.01207 0.00370 -0.1110 0.4005 0.0598
-1.500 0.4322 0.01200 0.00362 -0.1108 0.3987 0.0627
-1.250 0.4602 0.01192 0.00356 -0.1106 0.3967 0.0663
-1.000 0.4883 0.01188 0.00351 -0.1103 0.3945 0.0703
-0.750 0.5161 0.01182 0.00347 -0.1101 0.3922 0.0757
-0.500 0.5439 0.01179 0.00344 -0.1098 0.3899 0.0815
-0.250 0.5716 0.01177 0.00341 -0.1095 0.3877 0.0883
0.000 0.5991 0.01177 0.00341 -0.1092 0.3856 0.0973
0.250 0.6266 0.01176 0.00343 -0.1089 0.3837 0.1090
0.500 0.6546 0.01171 0.00344 -0.1087 0.3820 0.1239
0.750 0.6823 0.01166 0.00347 -0.1085 0.3801 0.1455
1.000 0.7101 0.01164 0.00352 -0.1082 0.3781 0.1690
1.250 0.7377 0.01163 0.00357 -0.1080 0.3760 0.1911
1.500 0.7651 0.01163 0.00363 -0.1077 0.3742 0.2135
1.750 0.7925 0.01165 0.00369 -0.1074 0.3723 0.2354
2.000 0.8197 0.01169 0.00376 -0.1071 0.3704 0.2561
2.250 0.8467 0.01174 0.00384 -0.1068 0.3683 0.2794
2.500 0.8738 0.01177 0.00394 -0.1065 0.3664 0.3083
2.750 0.9011 0.01174 0.00404 -0.1062 0.3646 0.3503
3.000 0.9279 0.01167 0.00416 -0.1059 0.3627 0.4176
3.250 0.9535 0.01151 0.00431 -0.1054 0.3608 0.5363
3.500 0.9734 0.01105 0.00449 -0.1036 0.3590 0.7769
4.000 1.0436 0.01102 0.00469 -0.1063 0.3547 1.0000
4.250 1.0703 0.01118 0.00480 -0.1059 0.3527 1.0000
4.500 1.0968 0.01136 0.00493 -0.1056 0.3506 1.0000
4.750 1.1241 0.01147 0.00505 -0.1053 0.3488 1.0000
5.000 1.1512 0.01160 0.00518 -0.1050 0.3465 1.0000
5.250 1.1780 0.01174 0.00531 -0.1047 0.3442 1.0000
5.500 1.2045 0.01189 0.00546 -0.1044 0.3420 1.0000
5.750 1.2308 0.01206 0.00560 -0.1040 0.3398 1.0000
6.000 1.2568 0.01223 0.00575 -0.1036 0.3376 1.0000
6.250 1.2823 0.01243 0.00592 -0.1031 0.3355 1.0000
6.500 1.3084 0.01260 0.00611 -0.1028 0.3336 1.0000
6.750 1.3346 0.01277 0.00630 -0.1024 0.3315 1.0000
7.000 1.3605 0.01294 0.00648 -0.1020 0.3291 1.0000
7.250 1.3859 0.01312 0.00668 -0.1016 0.3264 1.0000
7.500 1.4109 0.01331 0.00687 -0.1011 0.3237 1.0000
7.750 1.4353 0.01354 0.00708 -0.1005 0.3212 1.0000
8.000 1.4596 0.01377 0.00731 -0.0999 0.3190 1.0000
8.250 1.4847 0.01397 0.00755 -0.0994 0.3169 1.0000
8.500 1.5092 0.01417 0.00779 -0.0989 0.3145 1.0000
8.750 1.5333 0.01440 0.00805 -0.0983 0.3120 1.0000
9.000 1.5567 0.01464 0.00831 -0.0976 0.3095 1.0000
9.250 1.5793 0.01491 0.00858 -0.0968 0.3068 1.0000
9.500 1.6010 0.01522 0.00888 -0.0958 0.3042 1.0000
9.750 1.6242 0.01545 0.00918 -0.0951 0.3020 1.0000
10.000 1.6466 0.01572 0.00949 -0.0943 0.2995 1.0000
10.250 1.6681 0.01600 0.00982 -0.0934 0.2971 1.0000
10.500 1.6886 0.01631 0.01016 -0.0923 0.2946 1.0000
10.750 1.7078 0.01666 0.01052 -0.0910 0.2923 1.0000
11.000 1.7239 0.01704 0.01091 -0.0893 0.2898 1.0000
11.250 1.7418 0.01737 0.01130 -0.0878 0.2877 1.0000
11.500 1.7593 0.01772 0.01172 -0.0862 0.2855 1.0000
11.750 1.7755 0.01812 0.01217 -0.0846 0.2831 1.0000
12.000 1.7905 0.01857 0.01266 -0.0829 0.2806 1.0000
12.250 1.8030 0.01912 0.01323 -0.0809 0.2774 1.0000
12.500 1.8141 0.01976 0.01390 -0.0789 0.2741 1.0000
12.750 1.8280 0.02034 0.01455 -0.0774 0.2701 1.0000
13.000 1.8380 0.02113 0.01539 -0.0756 0.2655 1.0000
13.250 1.8440 0.02221 0.01648 -0.0737 0.2613 1.0000
13.500 1.8542 0.02320 0.01754 -0.0724 0.2574 1.0000
13.750 1.8628 0.02437 0.01879 -0.0712 0.2530 1.0000
14.000 1.8672 0.02597 0.02042 -0.0700 0.2488 1.0000
14.250 1.8709 0.02778 0.02229 -0.0691 0.2451 1.0000
14.500 1.8782 0.02943 0.02403 -0.0686 0.2411 1.0000
14.750 1.8802 0.03165 0.02632 -0.0682 0.2367 1.0000
15.000 1.8750 0.03469 0.02939 -0.0679 0.2321 1.0000
15.250 1.8748 0.03732 0.03212 -0.0677 0.2266 1.0000
15.500 1.8663 0.04086 0.03573 -0.0676 0.2212 1.0000
15.750 1.8530 0.04493 0.03986 -0.0676 0.2159 1.0000
16.000 1.8402 0.04898 0.04400 -0.0676 0.2096 1.0000
16.250 1.8173 0.05421 0.04928 -0.0677 0.2044 1.0000
16.500 1.8038 0.05851 0.05366 -0.0679 0.1984 1.0000
16.750 1.7809 0.06398 0.05918 -0.0683 0.1923 1.0000
17.000 1.7598 0.06935 0.06461 -0.0688 0.1850 1.0000
17.250 1.7338 0.07541 0.07070 -0.0695 0.1783 1.0000
17.500 1.7153 0.08066 0.07600 -0.0702 0.1712 1.0000
17.750 1.6900 0.08686 0.08222 -0.0711 0.1638 1.0000
18.000 1.6655 0.09307 0.08844 -0.0722 0.1550 1.0000
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