NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 200,000 Max Cl/Cd: 78.13 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632615-il-200000-n5.txt Download as CSV file: xf-naca632615-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-615
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5911 0.07400 0.06978 -0.0747 1.0000 0.0218
-13.250 -0.6201 0.06584 0.06149 -0.0801 1.0000 0.0216
-13.000 -0.6532 0.05820 0.05363 -0.0849 1.0000 0.0216
-12.750 -0.6768 0.05286 0.04810 -0.0875 1.0000 0.0217
-12.500 -0.6979 0.04849 0.04354 -0.0887 1.0000 0.0217
-12.250 -0.7195 0.04480 0.03964 -0.0886 1.0000 0.0219
-12.000 -0.7401 0.04218 0.03684 -0.0868 1.0000 0.0221
-11.750 -0.7416 0.04022 0.03482 -0.0868 0.9963 0.0224
-11.500 -0.7235 0.03808 0.03258 -0.0901 0.9858 0.0228
-11.250 -0.7056 0.03614 0.03049 -0.0929 0.9748 0.0234
-11.000 -0.6856 0.03390 0.02803 -0.0956 0.9645 0.0240
-10.750 -0.6634 0.03177 0.02563 -0.0979 0.9559 0.0248
-10.500 -0.6398 0.02968 0.02317 -0.0999 0.9478 0.0260
-10.250 -0.6144 0.02834 0.02170 -0.1014 0.9392 0.0270
-10.000 -0.5857 0.02722 0.02050 -0.1032 0.9322 0.0279
-9.750 -0.5596 0.02611 0.01923 -0.1043 0.9237 0.0292
-9.500 -0.5320 0.02483 0.01772 -0.1054 0.9161 0.0305
-9.250 -0.5069 0.02373 0.01647 -0.1059 0.9075 0.0316
-9.000 -0.4805 0.02292 0.01564 -0.1067 0.8995 0.0330
-8.750 -0.4561 0.02219 0.01481 -0.1068 0.8906 0.0346
-8.500 -0.4308 0.02140 0.01384 -0.1070 0.8825 0.0363
-8.250 -0.4079 0.02060 0.01297 -0.1067 0.8740 0.0376
-8.000 -0.3838 0.01994 0.01228 -0.1067 0.8659 0.0393
-7.750 -0.3601 0.01937 0.01163 -0.1064 0.8579 0.0413
-7.500 -0.3358 0.01879 0.01093 -0.1062 0.8501 0.0432
-7.250 -0.3124 0.01812 0.01023 -0.1060 0.8427 0.0453
-7.000 -0.2882 0.01761 0.00968 -0.1059 0.8349 0.0477
-6.750 -0.2626 0.01713 0.00909 -0.1058 0.8285 0.0503
-6.500 -0.2386 0.01659 0.00852 -0.1056 0.8206 0.0530
-6.250 -0.2127 0.01613 0.00800 -0.1057 0.8141 0.0564
-6.000 -0.1868 0.01574 0.00752 -0.1057 0.8072 0.0601
-5.750 -0.1609 0.01525 0.00703 -0.1058 0.8002 0.0652
-5.500 -0.1337 0.01487 0.00657 -0.1060 0.7943 0.0719
-5.250 -0.1074 0.01447 0.00618 -0.1061 0.7870 0.0818
-5.000 -0.0802 0.01402 0.00577 -0.1064 0.7807 0.0999
-4.750 -0.0530 0.01353 0.00540 -0.1068 0.7745 0.1353
-4.500 -0.0257 0.01297 0.00504 -0.1074 0.7678 0.1903
-4.250 0.0023 0.01229 0.00468 -0.1082 0.7621 0.2789
-4.000 0.0303 0.01179 0.00453 -0.1089 0.7555 0.3725
-3.750 0.0587 0.01160 0.00446 -0.1092 0.7492 0.4286
-3.250 0.1158 0.01150 0.00442 -0.1095 0.7371 0.4997
-3.000 0.1442 0.01151 0.00443 -0.1095 0.7310 0.5274
-2.750 0.1728 0.01154 0.00443 -0.1095 0.7257 0.5472
-2.500 0.2010 0.01157 0.00445 -0.1095 0.7192 0.5626
-2.250 0.2295 0.01161 0.00444 -0.1096 0.7134 0.5773
-2.000 0.2583 0.01164 0.00440 -0.1097 0.7077 0.5887
-1.750 0.2863 0.01165 0.00441 -0.1097 0.7014 0.5962
-1.500 0.3152 0.01168 0.00436 -0.1098 0.6960 0.6047
-1.250 0.3435 0.01170 0.00435 -0.1099 0.6903 0.6117
-1.000 0.3718 0.01173 0.00436 -0.1100 0.6840 0.6188
-0.750 0.4008 0.01176 0.00432 -0.1102 0.6787 0.6263
-0.500 0.4287 0.01179 0.00437 -0.1102 0.6732 0.6321
-0.250 0.4572 0.01184 0.00439 -0.1103 0.6670 0.6392
0.000 0.4857 0.01188 0.00439 -0.1105 0.6618 0.6457
0.250 0.5137 0.01193 0.00446 -0.1105 0.6562 0.6517
0.500 0.5422 0.01199 0.00450 -0.1107 0.6503 0.6591
0.750 0.5703 0.01205 0.00455 -0.1107 0.6451 0.6651
1.000 0.5983 0.01212 0.00464 -0.1107 0.6394 0.6717
1.250 0.6267 0.01220 0.00472 -0.1109 0.6336 0.6788
1.500 0.6544 0.01227 0.00480 -0.1108 0.6286 0.6848
1.750 0.6823 0.01236 0.00492 -0.1109 0.6229 0.6922
2.000 0.7100 0.01245 0.00504 -0.1109 0.6170 0.6987
2.250 0.7378 0.01254 0.00513 -0.1109 0.6119 0.7055
2.500 0.7657 0.01265 0.00528 -0.1110 0.6060 0.7133
2.750 0.7925 0.01274 0.00544 -0.1108 0.5999 0.7197
3.000 0.8205 0.01286 0.00555 -0.1108 0.5947 0.7272
3.250 0.8472 0.01297 0.00575 -0.1107 0.5882 0.7341
3.500 0.8740 0.01308 0.00591 -0.1105 0.5821 0.7418
3.750 0.9014 0.01321 0.00606 -0.1104 0.5766 0.7493
4.000 0.9272 0.01334 0.00629 -0.1101 0.5697 0.7566
4.250 0.9544 0.01347 0.00645 -0.1100 0.5633 0.7650
4.500 0.9796 0.01360 0.00667 -0.1095 0.5555 0.7723
4.750 1.0059 0.01373 0.00682 -0.1092 0.5467 0.7811
5.000 1.0300 0.01385 0.00705 -0.1085 0.5369 0.7886
5.250 1.0556 0.01401 0.00722 -0.1082 0.5275 0.7978
5.500 1.0789 0.01414 0.00745 -0.1073 0.5163 0.8058
5.750 1.1028 0.01431 0.00767 -0.1066 0.5040 0.8153
6.000 1.1249 0.01447 0.00790 -0.1055 0.4907 0.8244
6.250 1.1462 0.01467 0.00812 -0.1043 0.4731 0.8344
6.500 1.1649 0.01494 0.00835 -0.1027 0.4493 0.8453
6.750 1.1814 0.01526 0.00863 -0.1007 0.4210 0.8565
7.000 1.1968 0.01565 0.00898 -0.0986 0.3930 0.8693
7.250 1.2094 0.01611 0.00938 -0.0960 0.3637 0.8844
7.500 1.2175 0.01668 0.00984 -0.0927 0.3306 0.9044
7.750 1.2205 0.01731 0.01036 -0.0885 0.2975 0.9382
8.000 1.2252 0.01819 0.01109 -0.0853 0.2619 1.0000
8.250 1.2303 0.01938 0.01208 -0.0826 0.2265 1.0000
8.500 1.2351 0.02066 0.01319 -0.0800 0.1949 1.0000
9.000 1.2451 0.02342 0.01568 -0.0755 0.1421 1.0000
9.250 1.2503 0.02490 0.01708 -0.0735 0.1212 1.0000
9.500 1.2558 0.02644 0.01854 -0.0718 0.1027 1.0000
9.750 1.2612 0.02806 0.02010 -0.0701 0.0876 1.0000
10.000 1.2666 0.02975 0.02174 -0.0686 0.0754 1.0000
10.250 1.2726 0.03146 0.02344 -0.0673 0.0659 1.0000
10.500 1.2788 0.03321 0.02520 -0.0661 0.0589 1.0000
10.750 1.2839 0.03511 0.02710 -0.0650 0.0532 1.0000
11.000 1.2906 0.03692 0.02895 -0.0641 0.0485 1.0000
11.250 1.2958 0.03892 0.03098 -0.0632 0.0450 1.0000
11.500 1.3026 0.04083 0.03296 -0.0624 0.0419 1.0000
11.750 1.3069 0.04301 0.03517 -0.0617 0.0395 1.0000
12.000 1.3123 0.04516 0.03741 -0.0611 0.0375 1.0000
12.250 1.3181 0.04731 0.03965 -0.0606 0.0356 1.0000
12.500 1.3222 0.04969 0.04209 -0.0602 0.0339 1.0000
12.750 1.3244 0.05237 0.04482 -0.0599 0.0325 1.0000
13.000 1.3298 0.05475 0.04731 -0.0597 0.0311 1.0000
13.250 1.3341 0.05731 0.04997 -0.0595 0.0299 1.0000
13.500 1.3373 0.06005 0.05280 -0.0595 0.0288 1.0000
13.750 1.3390 0.06305 0.05587 -0.0596 0.0278 1.0000
14.000 1.3405 0.06613 0.05902 -0.0597 0.0270 1.0000
14.250 1.3443 0.06899 0.06202 -0.0599 0.0260 1.0000
14.500 1.3473 0.07201 0.06514 -0.0602 0.0251 1.0000
14.750 1.3498 0.07514 0.06836 -0.0606 0.0244 1.0000
15.000 1.3518 0.07839 0.07170 -0.0612 0.0237 1.0000
15.250 1.3526 0.08184 0.07521 -0.0618 0.0231 1.0000
15.500 1.3541 0.08523 0.07869 -0.0624 0.0225 1.0000
15.750 1.3571 0.08849 0.08210 -0.0631 0.0218 1.0000
16.000 1.3595 0.09188 0.08561 -0.0639 0.0212 1.0000
16.250 1.3615 0.09537 0.08922 -0.0648 0.0206 1.0000
16.500 1.3629 0.09898 0.09293 -0.0659 0.0200 1.0000
16.750 1.3640 0.10266 0.09670 -0.0671 0.0196 1.0000
17.000 1.3648 0.10644 0.10056 -0.0685 0.0192 1.0000
17.250 1.3657 0.11014 0.10431 -0.0698 0.0189 1.0000
17.500 1.3666 0.11396 0.10829 -0.0712 0.0185 1.0000
17.750 1.3666 0.11798 0.11248 -0.0727 0.0182 1.0000
18.000 1.3661 0.12211 0.11677 -0.0745 0.0179 1.0000
18.250 1.3649 0.12642 0.12124 -0.0764 0.0176 1.0000
18.500 1.3631 0.13091 0.12589 -0.0786 0.0173 1.0000
18.750 1.3606 0.13558 0.13070 -0.0810 0.0171 1.0000
19.000 1.3576 0.14040 0.13568 -0.0837 0.0169 1.0000
19.250 1.3539 0.14544 0.14087 -0.0866 0.0167 1.0000
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Polar data table (+)
Polar graphs
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