NACA 63-215 AIRFOIL (n63215-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-215 AIRFOIL (n63215-il) Reynolds number: 100,000 Max Cl/Cd: 48.62 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63215-il-100000.txt Download as CSV file: xf-n63215-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-215 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5394 0.12898 0.12378 -0.0174 1.0000 0.1579
-12.250 -0.5709 0.08318 0.07827 -0.0459 1.0000 0.0854
-12.000 -0.5852 0.07613 0.07119 -0.0483 1.0000 0.0843
-11.750 -0.6123 0.06833 0.06332 -0.0515 1.0000 0.0827
-11.500 -0.6516 0.06033 0.05520 -0.0546 1.0000 0.0804
-11.250 -0.8372 0.06245 0.05625 -0.0522 1.0000 0.0736
-11.000 -0.8388 0.05782 0.05148 -0.0516 1.0000 0.0730
-10.750 -0.8428 0.05406 0.04751 -0.0504 1.0000 0.0726
-10.500 -0.8474 0.05086 0.04400 -0.0487 1.0000 0.0727
-10.250 -0.8497 0.04811 0.04089 -0.0467 1.0000 0.0732
-10.000 -0.8488 0.04533 0.03776 -0.0446 1.0000 0.0740
-9.750 -0.8394 0.04186 0.03413 -0.0435 1.0000 0.0751
-9.500 -0.8289 0.03943 0.03157 -0.0418 1.0000 0.0762
-9.250 -0.8196 0.03750 0.02951 -0.0397 1.0000 0.0774
-9.000 -0.8126 0.03594 0.02784 -0.0370 1.0000 0.0789
-8.750 -0.8084 0.03471 0.02647 -0.0339 1.0000 0.0809
-8.500 -0.8047 0.03356 0.02512 -0.0306 1.0000 0.0832
-8.250 -0.7988 0.03244 0.02374 -0.0277 1.0000 0.0851
-8.000 -0.7869 0.03072 0.02194 -0.0256 1.0000 0.0873
-7.750 -0.7746 0.02949 0.02080 -0.0237 1.0000 0.0906
-7.500 -0.7632 0.02860 0.01982 -0.0217 1.0000 0.0947
-7.250 -0.7507 0.02780 0.01883 -0.0197 1.0000 0.0986
-7.000 -0.7220 0.02633 0.01756 -0.0206 0.9966 0.1051
-6.750 -0.6838 0.02508 0.01633 -0.0232 0.9901 0.1156
-6.500 -0.6457 0.02385 0.01524 -0.0260 0.9834 0.1300
-6.250 -0.6140 0.02255 0.01416 -0.0279 0.9751 0.1540
-6.000 -0.5874 0.02030 0.01267 -0.0299 0.9671 0.2297
-5.750 -0.5646 0.01874 0.01241 -0.0307 0.9581 0.4455
-5.500 -0.5316 0.01918 0.01287 -0.0314 0.9492 0.5084
-5.250 -0.4912 0.01987 0.01350 -0.0331 0.9424 0.5468
-5.000 -0.4599 0.02053 0.01409 -0.0331 0.9337 0.5736
-4.750 -0.4189 0.02144 0.01496 -0.0343 0.9275 0.6000
-4.500 -0.3872 0.02224 0.01572 -0.0339 0.9197 0.6208
-4.250 -0.3503 0.02308 0.01654 -0.0340 0.9129 0.6383
-4.000 -0.3158 0.02362 0.01700 -0.0343 0.9063 0.6538
-3.750 -0.2858 0.02420 0.01754 -0.0334 0.8981 0.6652
-3.500 -0.2455 0.02465 0.01793 -0.0342 0.8934 0.6769
-3.250 -0.2270 0.02476 0.01795 -0.0326 0.8829 0.6889
-3.000 -0.1900 0.02490 0.01801 -0.0334 0.8777 0.6983
-2.750 -0.1714 0.02495 0.01800 -0.0319 0.8676 0.7071
-2.500 -0.1383 0.02484 0.01779 -0.0327 0.8619 0.7168
-2.250 -0.1194 0.02492 0.01784 -0.0312 0.8523 0.7243
-2.000 -0.0891 0.02478 0.01762 -0.0316 0.8462 0.7334
-1.750 -0.0694 0.02484 0.01764 -0.0303 0.8372 0.7408
-1.500 -0.0416 0.02474 0.01748 -0.0302 0.8306 0.7493
-1.250 -0.0196 0.02475 0.01745 -0.0294 0.8230 0.7570
-1.000 0.0042 0.02474 0.01741 -0.0287 0.8153 0.7651
-0.750 0.0353 0.02452 0.01713 -0.0290 0.8108 0.7729
-0.500 0.0493 0.02477 0.01740 -0.0273 0.8004 0.7808
-0.250 0.0791 0.02455 0.01713 -0.0275 0.7955 0.7890
0.000 0.0946 0.02482 0.01742 -0.0259 0.7859 0.7968
0.250 0.1219 0.02468 0.01725 -0.0258 0.7802 0.8054
0.500 0.1419 0.02487 0.01745 -0.0246 0.7727 0.8131
0.750 0.1640 0.02489 0.01747 -0.0240 0.7653 0.8220
1.000 0.1948 0.02472 0.01730 -0.0237 0.7613 0.8297
1.250 0.2058 0.02515 0.01778 -0.0221 0.7509 0.8392
1.500 0.2349 0.02500 0.01762 -0.0218 0.7461 0.8480
1.750 0.2491 0.02538 0.01806 -0.0202 0.7372 0.8574
2.000 0.2742 0.02533 0.01802 -0.0197 0.7310 0.8678
2.250 0.3078 0.02504 0.01775 -0.0196 0.7275 0.8753
2.500 0.3149 0.02568 0.01847 -0.0174 0.7162 0.8873
2.750 0.3479 0.02537 0.01818 -0.0175 0.7121 0.8971
3.000 0.3602 0.02597 0.01888 -0.0160 0.7016 0.9090
3.250 0.3957 0.02568 0.01863 -0.0167 0.6967 0.9187
3.500 0.4165 0.02612 0.01916 -0.0164 0.6874 0.9314
3.750 0.4575 0.02589 0.01900 -0.0183 0.6814 0.9409
4.000 0.4988 0.02590 0.01909 -0.0208 0.6740 0.9500
4.250 0.5413 0.02575 0.01905 -0.0234 0.6655 0.9594
4.500 0.5919 0.02548 0.01888 -0.0272 0.6565 0.9666
4.750 0.6470 0.02457 0.01805 -0.0309 0.6476 0.9727
5.000 0.6956 0.02414 0.01774 -0.0345 0.6348 0.9806
5.250 0.7467 0.02330 0.01701 -0.0379 0.6221 0.9881
5.500 0.7961 0.02223 0.01600 -0.0408 0.6069 0.9966
5.750 0.8240 0.02142 0.01521 -0.0402 0.5918 1.0000
6.000 0.8382 0.02080 0.01459 -0.0374 0.5769 1.0000
6.250 0.8494 0.02029 0.01408 -0.0342 0.5605 1.0000
6.500 0.8587 0.01991 0.01371 -0.0309 0.5435 1.0000
6.750 0.8703 0.01959 0.01342 -0.0280 0.5242 1.0000
7.000 0.8906 0.01918 0.01301 -0.0263 0.5009 1.0000
7.250 0.9091 0.01904 0.01292 -0.0248 0.4707 1.0000
7.500 0.9262 0.01905 0.01290 -0.0231 0.4283 1.0000
7.750 0.9367 0.01948 0.01303 -0.0205 0.3570 1.0000
8.000 0.9322 0.02112 0.01391 -0.0166 0.2570 1.0000
8.250 0.9232 0.02334 0.01548 -0.0127 0.1919 1.0000
8.500 0.9185 0.02528 0.01700 -0.0093 0.1591 1.0000
8.750 0.9230 0.02700 0.01850 -0.0069 0.1373 1.0000
9.000 0.9335 0.02855 0.01990 -0.0053 0.1225 1.0000
9.250 0.9499 0.03007 0.02126 -0.0043 0.1114 1.0000
9.500 0.9720 0.03158 0.02259 -0.0038 0.1019 1.0000
9.750 0.9944 0.03299 0.02411 -0.0033 0.0945 1.0000
10.000 1.0286 0.03492 0.02586 -0.0042 0.0873 1.0000
10.250 1.0499 0.03647 0.02761 -0.0037 0.0823 1.0000
10.500 1.0853 0.03864 0.02969 -0.0051 0.0773 1.0000
10.750 1.1081 0.04101 0.03230 -0.0049 0.0738 1.0000
11.000 1.1244 0.04309 0.03463 -0.0040 0.0711 1.0000
11.250 1.1436 0.04552 0.03726 -0.0035 0.0690 1.0000
11.500 1.1610 0.04807 0.03994 -0.0031 0.0671 1.0000
11.750 1.1852 0.05256 0.04450 -0.0041 0.0651 1.0000
12.000 1.1783 0.05471 0.04702 -0.0011 0.0645 1.0000
12.250 1.1677 0.05720 0.04984 0.0018 0.0639 1.0000
12.500 1.1567 0.06019 0.05315 0.0039 0.0636 1.0000
12.750 1.1428 0.06355 0.05680 0.0056 0.0634 1.0000
13.000 1.1269 0.06739 0.06091 0.0066 0.0634 1.0000
13.250 1.1091 0.07168 0.06545 0.0070 0.0636 1.0000
13.500 1.0897 0.07643 0.07043 0.0068 0.0638 1.0000
13.750 1.0691 0.08169 0.07590 0.0058 0.0642 1.0000
14.000 1.0497 0.08745 0.08184 0.0042 0.0646 1.0000
14.250 1.0335 0.09378 0.08830 0.0023 0.0650 1.0000
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