FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-K-170/22 (fx73k170-il) Reynolds number: 200,000 Max Cl/Cd: 65.58 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73k170-il-200000-n5.txt Download as CSV file: xf-fx73k170-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-K-170/22
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1604 0.06478 0.05989 -0.1464 0.8198 0.0135
-11.500 -0.1801 0.05826 0.05325 -0.1512 0.8175 0.0135
-11.250 -0.1914 0.05407 0.04898 -0.1537 0.8146 0.0133
-11.000 -0.2092 0.04967 0.04443 -0.1559 0.8113 0.0133
-10.750 -0.2221 0.04619 0.04080 -0.1570 0.8083 0.0132
-10.500 -0.2410 0.04250 0.03684 -0.1572 0.8055 0.0133
-10.250 -0.2517 0.03984 0.03399 -0.1565 0.8026 0.0132
-10.000 -0.2579 0.03797 0.03201 -0.1549 0.7991 0.0131
-9.750 -0.2711 0.03597 0.02977 -0.1520 0.7956 0.0132
-9.500 -0.2731 0.03409 0.02765 -0.1498 0.7926 0.0132
-9.250 -0.2685 0.03228 0.02557 -0.1481 0.7903 0.0132
-9.000 -0.2602 0.03044 0.02340 -0.1467 0.7884 0.0133
-8.750 -0.2505 0.02894 0.02168 -0.1449 0.7852 0.0134
-8.500 -0.2368 0.02763 0.02015 -0.1435 0.7822 0.0135
-8.250 -0.2205 0.02632 0.01869 -0.1425 0.7796 0.0137
-8.000 -0.2027 0.02513 0.01740 -0.1416 0.7774 0.0140
-7.750 -0.1831 0.02419 0.01636 -0.1409 0.7754 0.0143
-7.500 -0.1627 0.02333 0.01540 -0.1403 0.7737 0.0149
-7.250 -0.1446 0.02257 0.01457 -0.1392 0.7712 0.0153
-7.000 -0.1270 0.02189 0.01382 -0.1379 0.7681 0.0160
-6.750 -0.1083 0.02120 0.01305 -0.1368 0.7652 0.0166
-6.500 -0.0883 0.02055 0.01232 -0.1360 0.7627 0.0177
-6.250 -0.0670 0.02000 0.01175 -0.1355 0.7607 0.0194
-6.000 -0.0444 0.01946 0.01113 -0.1351 0.7590 0.0212
-5.750 -0.0226 0.01894 0.01050 -0.1346 0.7571 0.0225
-5.500 -0.0048 0.01845 0.01003 -0.1334 0.7536 0.0248
-5.250 0.0166 0.01804 0.00954 -0.1326 0.7506 0.0283
-5.000 0.0390 0.01756 0.00905 -0.1322 0.7480 0.0350
-4.750 0.0624 0.01703 0.00856 -0.1319 0.7459 0.0511
-4.500 0.0865 0.01648 0.00811 -0.1318 0.7442 0.0840
-4.250 0.1099 0.01575 0.00767 -0.1318 0.7427 0.1549
-4.000 0.1242 0.01498 0.00748 -0.1305 0.7388 0.2832
-3.750 0.1408 0.01427 0.00741 -0.1292 0.7356 0.4330
-3.500 0.1643 0.01422 0.00757 -0.1284 0.7330 0.5077
-3.250 0.1910 0.01430 0.00763 -0.1281 0.7309 0.5471
-3.000 0.2189 0.01443 0.00768 -0.1280 0.7293 0.5727
-2.750 0.2475 0.01459 0.00773 -0.1280 0.7278 0.5951
-2.500 0.2682 0.01488 0.00803 -0.1267 0.7240 0.6079
-2.250 0.2920 0.01504 0.00814 -0.1260 0.7206 0.6177
-2.000 0.3182 0.01512 0.00813 -0.1257 0.7181 0.6262
-1.750 0.3455 0.01515 0.00808 -0.1257 0.7161 0.6323
-1.500 0.3740 0.01515 0.00802 -0.1258 0.7144 0.6376
-1.250 0.4036 0.01511 0.00784 -0.1263 0.7129 0.6439
-1.000 0.4222 0.01532 0.00808 -0.1248 0.7084 0.6478
-0.750 0.4460 0.01540 0.00814 -0.1242 0.7052 0.6516
-0.500 0.4725 0.01540 0.00809 -0.1241 0.7027 0.6559
-0.250 0.5007 0.01537 0.00796 -0.1244 0.7007 0.6605
0.000 0.5298 0.01532 0.00786 -0.1248 0.6990 0.6634
0.250 0.5530 0.01542 0.00797 -0.1241 0.6961 0.6665
0.500 0.5728 0.01559 0.00816 -0.1229 0.6920 0.6699
0.750 0.5977 0.01563 0.00817 -0.1226 0.6891 0.6734
1.000 0.6252 0.01562 0.00810 -0.1228 0.6869 0.6768
1.250 0.6543 0.01556 0.00803 -0.1231 0.6850 0.6792
1.500 0.6829 0.01553 0.00798 -0.1235 0.6831 0.6818
1.750 0.6971 0.01583 0.00836 -0.1212 0.6782 0.6847
2.000 0.7202 0.01592 0.00845 -0.1206 0.6750 0.6878
2.250 0.7474 0.01591 0.00842 -0.1207 0.6725 0.6911
2.500 0.7772 0.01584 0.00834 -0.1213 0.6704 0.6938
2.750 0.8028 0.01587 0.00839 -0.1211 0.6677 0.6961
3.000 0.8157 0.01617 0.00877 -0.1186 0.6626 0.6991
3.250 0.8399 0.01622 0.00884 -0.1181 0.6593 0.7022
3.500 0.8687 0.01617 0.00879 -0.1185 0.6567 0.7055
3.750 0.9009 0.01608 0.00868 -0.1195 0.6546 0.7083
4.000 0.9095 0.01645 0.00916 -0.1163 0.6490 0.7110
4.250 0.9304 0.01656 0.00932 -0.1152 0.6450 0.7139
4.500 0.9588 0.01652 0.00933 -0.1155 0.6421 0.7173
4.750 0.9923 0.01641 0.00922 -0.1167 0.6397 0.7205
5.000 0.9947 0.01687 0.00976 -0.1124 0.6333 0.7239
5.250 1.0157 0.01693 0.00990 -0.1114 0.6290 0.7268
5.500 1.0474 0.01685 0.00987 -0.1122 0.6259 0.7303
5.750 1.0607 0.01713 0.01022 -0.1099 0.6209 0.7342
6.000 1.0736 0.01745 0.01062 -0.1076 0.6153 0.7381
6.250 1.1028 0.01738 0.01061 -0.1080 0.6113 0.7414
6.500 1.1149 0.01773 0.01106 -0.1055 0.6052 0.7452
6.750 1.1303 0.01800 0.01140 -0.1037 0.5986 0.7499
7.000 1.1661 0.01778 0.01122 -0.1051 0.5945 0.7546
7.250 1.1635 0.01862 0.01220 -0.1007 0.5851 0.7595
7.500 1.1975 0.01839 0.01201 -0.1018 0.5797 0.7644
7.750 1.1983 0.01932 0.01306 -0.0984 0.5698 0.7705
8.000 1.2217 0.01949 0.01331 -0.0981 0.5615 0.7760
8.250 1.2386 0.01992 0.01383 -0.0970 0.5510 0.7831
8.500 1.2501 0.02070 0.01472 -0.0954 0.5396 0.7911
8.750 1.2653 0.02132 0.01543 -0.0944 0.5268 0.8012
9.000 1.2820 0.02193 0.01612 -0.0936 0.5119 0.8131
9.250 1.2989 0.02254 0.01676 -0.0929 0.4923 0.8284
9.500 1.3139 0.02342 0.01766 -0.0922 0.4654 0.8526
9.750 1.3306 0.02465 0.01885 -0.0930 0.4254 0.9882
10.000 1.3269 0.02606 0.02012 -0.0891 0.4011 1.0000
10.250 1.3265 0.02780 0.02171 -0.0866 0.3720 1.0000
10.500 1.3253 0.02967 0.02345 -0.0842 0.3442 1.0000
10.750 1.3250 0.03158 0.02525 -0.0820 0.3201 1.0000
11.000 1.3216 0.03381 0.02735 -0.0797 0.2921 1.0000
11.250 1.3174 0.03622 0.02964 -0.0776 0.2635 1.0000
11.500 1.3151 0.03860 0.03191 -0.0757 0.2375 1.0000
11.750 1.3120 0.04113 0.03432 -0.0739 0.2116 1.0000
12.000 1.3093 0.04373 0.03680 -0.0723 0.1867 1.0000
12.250 1.3063 0.04642 0.03938 -0.0708 0.1616 1.0000
12.500 1.3033 0.04918 0.04201 -0.0694 0.1374 1.0000
12.750 1.3023 0.05182 0.04457 -0.0682 0.1175 1.0000
13.000 1.3016 0.05451 0.04717 -0.0671 0.0978 1.0000
13.250 1.3013 0.05719 0.04979 -0.0662 0.0821 1.0000
13.500 1.3008 0.05995 0.05250 -0.0652 0.0687 1.0000
13.750 1.3019 0.06260 0.05513 -0.0645 0.0578 1.0000
14.000 1.3042 0.06517 0.05774 -0.0639 0.0505 1.0000
14.250 1.3053 0.06792 0.06049 -0.0633 0.0441 1.0000
14.500 1.3070 0.07064 0.06324 -0.0628 0.0388 1.0000
14.750 1.3083 0.07345 0.06611 -0.0624 0.0355 1.0000
15.000 1.3112 0.07611 0.06886 -0.0621 0.0322 1.0000
15.250 1.3111 0.07918 0.07196 -0.0618 0.0295 1.0000
15.500 1.3136 0.08198 0.07486 -0.0616 0.0270 1.0000
15.750 1.3157 0.08483 0.07779 -0.0616 0.0246 1.0000
16.000 1.3143 0.08815 0.08116 -0.0615 0.0227 1.0000
16.250 1.3149 0.09127 0.08442 -0.0616 0.0213 1.0000
16.500 1.3160 0.09437 0.08762 -0.0617 0.0198 1.0000
16.750 1.3159 0.09765 0.09100 -0.0620 0.0184 1.0000
17.000 1.3124 0.10144 0.09484 -0.0624 0.0173 1.0000
17.250 1.3117 0.10490 0.09843 -0.0629 0.0165 1.0000
17.500 1.3114 0.10830 0.10196 -0.0633 0.0154 1.0000
17.750 1.3107 0.11180 0.10557 -0.0640 0.0145 1.0000
18.000 1.3096 0.11539 0.10927 -0.0648 0.0141 1.0000
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