FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 73-CL1-152 (fx73cl1152-il) Reynolds number: 500,000 Max Cl/Cd: 100.82 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73cl1152-il-500000.txt Download as CSV file: xf-fx73cl1152-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0429 0.09916 0.09471 -0.0701 0.5414 0.0412
-9.750 -0.0337 0.09690 0.09240 -0.0709 0.5338 0.0421
-9.500 -0.0578 0.09030 0.08585 -0.0770 0.5336 0.0448
-9.250 -0.0458 0.08805 0.08358 -0.0770 0.5264 0.0450
-9.000 -0.0308 0.08649 0.08198 -0.0766 0.5191 0.0453
-8.750 -0.0180 0.08472 0.08014 -0.0766 0.5124 0.0456
-8.500 -0.2796 0.03080 0.02570 -0.1175 0.5468 0.0397
-8.250 -0.2730 0.02655 0.02093 -0.1189 0.5394 0.0400
-8.000 -0.2539 0.02486 0.01903 -0.1188 0.5311 0.0404
-7.750 -0.2309 0.02385 0.01793 -0.1187 0.5236 0.0409
-7.500 -0.2071 0.02312 0.01708 -0.1184 0.5161 0.0414
-7.250 -0.1832 0.02224 0.01605 -0.1182 0.5098 0.0419
-7.000 -0.1592 0.02117 0.01478 -0.1180 0.5038 0.0426
-6.750 -0.1349 0.02017 0.01354 -0.1177 0.4982 0.0434
-6.500 -0.1100 0.01938 0.01247 -0.1174 0.4928 0.0442
-6.250 -0.0843 0.01848 0.01135 -0.1172 0.4883 0.0449
-6.000 -0.0589 0.01758 0.01040 -0.1169 0.4835 0.0456
-5.750 -0.0324 0.01716 0.00990 -0.1166 0.4788 0.0464
-5.500 -0.0059 0.01680 0.00942 -0.1162 0.4743 0.0472
-5.250 0.0213 0.01633 0.00888 -0.1159 0.4711 0.0481
-5.000 0.0486 0.01589 0.00834 -0.1156 0.4676 0.0491
-4.750 0.0762 0.01561 0.00791 -0.1153 0.4641 0.0500
-4.500 0.1026 0.01499 0.00726 -0.1150 0.4608 0.0512
-4.250 0.1298 0.01480 0.00701 -0.1147 0.4572 0.0524
-4.000 0.1574 0.01455 0.00672 -0.1144 0.4544 0.0537
-3.750 0.1852 0.01428 0.00640 -0.1141 0.4516 0.0550
-3.500 0.2131 0.01404 0.00609 -0.1137 0.4487 0.0562
-3.250 0.2402 0.01362 0.00569 -0.1134 0.4460 0.0578
-3.000 0.2680 0.01349 0.00553 -0.1132 0.4434 0.0597
-2.750 0.2958 0.01340 0.00536 -0.1128 0.4407 0.0617
-2.500 0.3230 0.01325 0.00515 -0.1125 0.4375 0.0638
-2.250 0.3509 0.01305 0.00499 -0.1123 0.4356 0.0661
-2.000 0.3790 0.01292 0.00485 -0.1120 0.4333 0.0689
-1.750 0.4067 0.01271 0.00465 -0.1117 0.4310 0.0722
-1.500 0.4346 0.01262 0.00456 -0.1115 0.4286 0.0762
-1.250 0.4624 0.01247 0.00440 -0.1112 0.4261 0.0808
-1.000 0.4902 0.01242 0.00433 -0.1109 0.4237 0.0862
-0.750 0.5178 0.01239 0.00429 -0.1106 0.4210 0.0937
-0.500 0.5455 0.01237 0.00429 -0.1104 0.4185 0.1028
-0.250 0.5734 0.01226 0.00424 -0.1101 0.4167 0.1148
0.000 0.6011 0.01216 0.00422 -0.1099 0.4147 0.1327
0.250 0.6288 0.01208 0.00424 -0.1096 0.4126 0.1611
0.500 0.6564 0.01203 0.00427 -0.1094 0.4102 0.1917
0.750 0.6841 0.01201 0.00431 -0.1091 0.4080 0.2194
1.250 0.7392 0.01211 0.00446 -0.1086 0.4037 0.2695
1.500 0.7667 0.01225 0.00465 -0.1084 0.4012 0.3008
1.750 0.7939 0.01218 0.00472 -0.1081 0.3998 0.3420
2.000 0.8208 0.01209 0.00481 -0.1078 0.3978 0.3998
2.250 0.8470 0.01193 0.00492 -0.1073 0.3957 0.4937
2.500 0.8699 0.01156 0.00507 -0.1062 0.3935 0.6800
2.750 0.9100 0.01110 0.00515 -0.1084 0.3912 1.0000
3.000 0.9376 0.01123 0.00522 -0.1081 0.3892 1.0000
3.250 0.9650 0.01141 0.00532 -0.1079 0.3872 1.0000
3.500 0.9925 0.01171 0.00554 -0.1077 0.3846 1.0000
3.750 1.0198 0.01186 0.00568 -0.1074 0.3829 1.0000
4.000 1.0470 0.01196 0.00578 -0.1071 0.3811 1.0000
4.250 1.0741 0.01207 0.00589 -0.1068 0.3789 1.0000
4.500 1.1011 0.01219 0.00599 -0.1065 0.3766 1.0000
4.750 1.1281 0.01232 0.00609 -0.1062 0.3743 1.0000
5.000 1.1550 0.01245 0.00619 -0.1059 0.3721 1.0000
5.250 1.1818 0.01265 0.00634 -0.1056 0.3700 1.0000
5.500 1.2087 0.01301 0.00663 -0.1054 0.3672 1.0000
5.750 1.2350 0.01312 0.00678 -0.1050 0.3656 1.0000
6.000 1.2612 0.01324 0.00694 -0.1046 0.3635 1.0000
6.250 1.2874 0.01338 0.00710 -0.1043 0.3613 1.0000
6.500 1.3135 0.01353 0.00726 -0.1039 0.3589 1.0000
6.750 1.3396 0.01368 0.00739 -0.1035 0.3566 1.0000
7.000 1.3654 0.01385 0.00754 -0.1031 0.3543 1.0000
7.250 1.3913 0.01415 0.00779 -0.1028 0.3515 1.0000
7.500 1.4165 0.01436 0.00804 -0.1023 0.3494 1.0000
7.750 1.4415 0.01452 0.00825 -0.1018 0.3472 1.0000
8.000 1.4664 0.01469 0.00846 -0.1013 0.3447 1.0000
8.250 1.4913 0.01487 0.00866 -0.1008 0.3424 1.0000
8.500 1.5160 0.01505 0.00885 -0.1002 0.3401 1.0000
8.750 1.5405 0.01528 0.00907 -0.0997 0.3377 1.0000
9.000 1.5653 0.01568 0.00942 -0.0993 0.3348 1.0000
9.250 1.5883 0.01585 0.00968 -0.0985 0.3327 1.0000
9.500 1.6114 0.01606 0.00996 -0.0978 0.3303 1.0000
9.750 1.6345 0.01629 0.01023 -0.0971 0.3279 1.0000
10.000 1.6574 0.01652 0.01049 -0.0963 0.3255 1.0000
10.250 1.6800 0.01678 0.01076 -0.0956 0.3233 1.0000
10.500 1.7026 0.01713 0.01109 -0.0948 0.3208 1.0000
10.750 1.7243 0.01750 0.01150 -0.0940 0.3184 1.0000
11.000 1.7444 0.01777 0.01187 -0.0929 0.3161 1.0000
11.250 1.7645 0.01807 0.01224 -0.0918 0.3138 1.0000
11.500 1.7842 0.01838 0.01259 -0.0906 0.3115 1.0000
11.750 1.8029 0.01868 0.01293 -0.0893 0.3091 1.0000
12.000 1.8200 0.01903 0.01327 -0.0877 0.3065 1.0000
12.250 1.8358 0.01947 0.01373 -0.0860 0.3034 1.0000
12.500 1.8468 0.01980 0.01418 -0.0835 0.3005 1.0000
12.750 1.8588 0.02018 0.01462 -0.0813 0.2971 1.0000
13.000 1.8704 0.02062 0.01510 -0.0793 0.2936 1.0000
13.250 1.8823 0.02124 0.01568 -0.0774 0.2897 1.0000
13.500 1.8918 0.02190 0.01646 -0.0754 0.2869 1.0000
13.750 1.9012 0.02264 0.01730 -0.0736 0.2834 1.0000
14.000 1.9102 0.02351 0.01823 -0.0720 0.2800 1.0000
14.250 1.9176 0.02458 0.01929 -0.0705 0.2765 1.0000
14.500 1.9246 0.02580 0.02060 -0.0692 0.2729 1.0000
14.750 1.9307 0.02721 0.02212 -0.0682 0.2690 1.0000
15.000 1.9348 0.02887 0.02385 -0.0674 0.2647 1.0000
15.250 1.9352 0.03095 0.02592 -0.0665 0.2600 1.0000
15.500 1.9384 0.03305 0.02817 -0.0662 0.2561 1.0000
15.750 1.9379 0.03553 0.03073 -0.0660 0.2516 1.0000
16.000 1.9345 0.03830 0.03353 -0.0656 0.2478 1.0000
16.250 1.9307 0.04119 0.03651 -0.0654 0.2442 1.0000
16.500 1.9260 0.04430 0.03975 -0.0654 0.2403 1.0000
16.750 1.9168 0.04784 0.04336 -0.0653 0.2361 1.0000
17.000 1.9040 0.05173 0.04726 -0.0653 0.2320 1.0000
17.250 1.8936 0.05569 0.05137 -0.0656 0.2278 1.0000
17.500 1.8776 0.06029 0.05605 -0.0659 0.2227 1.0000
17.750 1.8613 0.06490 0.06067 -0.0663 0.2181 1.0000
18.000 1.8462 0.06960 0.06551 -0.0668 0.2133 1.0000
18.250 1.8256 0.07496 0.07092 -0.0675 0.2073 1.0000
18.500 1.8073 0.08013 0.07615 -0.0683 0.2014 1.0000
18.750 1.7865 0.08571 0.08179 -0.0692 0.1948 1.0000
19.000 1.7654 0.09140 0.08752 -0.0702 0.1879 1.0000
19.250 1.7422 0.09749 0.09363 -0.0715 0.1801 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 73-CL1-152 (fx73cl1152-il)