NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-412 AIRFOIL (n63412-il) Reynolds number: 500,000 Max Cl/Cd: 99.76 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63412-il-500000.txt Download as CSV file: xf-n63412-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-412 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4722 0.08792 0.08560 -0.0423 1.0000 0.0281
-10.250 -0.6475 0.04785 0.04503 -0.0681 1.0000 0.0183
-10.000 -0.6706 0.04488 0.04194 -0.0661 1.0000 0.0182
-9.750 -0.6890 0.04136 0.03822 -0.0638 1.0000 0.0181
-9.500 -0.7076 0.03848 0.03516 -0.0597 1.0000 0.0180
-9.250 -0.6960 0.03218 0.02826 -0.0632 0.9947 0.0180
-9.000 -0.6719 0.02807 0.02359 -0.0659 0.9888 0.0185
-8.750 -0.6445 0.02423 0.01927 -0.0687 0.9845 0.0193
-8.500 -0.6128 0.02304 0.01801 -0.0708 0.9802 0.0201
-8.250 -0.5800 0.02191 0.01679 -0.0727 0.9756 0.0210
-8.000 -0.5458 0.02029 0.01496 -0.0748 0.9719 0.0218
-7.750 -0.5139 0.01894 0.01341 -0.0761 0.9653 0.0228
-7.500 -0.4805 0.01799 0.01227 -0.0776 0.9586 0.0236
-7.250 -0.4521 0.01622 0.01039 -0.0784 0.9500 0.0249
-7.000 -0.4217 0.01553 0.00968 -0.0793 0.9418 0.0262
-6.750 -0.3950 0.01489 0.00897 -0.0793 0.9310 0.0274
-6.500 -0.3686 0.01428 0.00826 -0.0792 0.9212 0.0286
-6.250 -0.3424 0.01380 0.00768 -0.0789 0.9116 0.0297
-6.000 -0.3192 0.01283 0.00664 -0.0784 0.9012 0.0316
-5.750 -0.2936 0.01235 0.00611 -0.0781 0.8923 0.0335
-5.500 -0.2679 0.01194 0.00564 -0.0778 0.8828 0.0354
-5.250 -0.2415 0.01160 0.00521 -0.0776 0.8741 0.0374
-5.000 -0.2159 0.01099 0.00454 -0.0774 0.8658 0.0408
-4.750 -0.1892 0.01067 0.00418 -0.0773 0.8571 0.0449
-4.500 -0.1622 0.01032 0.00375 -0.0772 0.8494 0.0498
-4.250 -0.1351 0.00998 0.00341 -0.0772 0.8409 0.0582
-4.000 -0.1080 0.00952 0.00302 -0.0773 0.8337 0.0865
-3.750 -0.0819 0.00864 0.00264 -0.0777 0.8253 0.2049
-3.500 -0.0559 0.00774 0.00232 -0.0781 0.8182 0.3748
-3.250 -0.0285 0.00737 0.00224 -0.0783 0.8099 0.4647
-3.000 -0.0006 0.00726 0.00217 -0.0783 0.8030 0.5087
-2.750 0.0276 0.00718 0.00214 -0.0784 0.7949 0.5394
-2.500 0.0557 0.00716 0.00209 -0.0783 0.7880 0.5625
-2.250 0.0841 0.00714 0.00206 -0.0784 0.7800 0.5820
-2.000 0.1120 0.00712 0.00205 -0.0783 0.7730 0.6057
-1.750 0.1401 0.00710 0.00206 -0.0783 0.7652 0.6261
-1.500 0.1683 0.00713 0.00206 -0.0782 0.7581 0.6436
-1.250 0.1965 0.00714 0.00208 -0.0782 0.7504 0.6578
-1.000 0.2246 0.00716 0.00208 -0.0781 0.7433 0.6678
-0.750 0.2530 0.00718 0.00209 -0.0782 0.7357 0.6779
-0.500 0.2814 0.00722 0.00208 -0.0782 0.7284 0.6878
-0.250 0.3096 0.00722 0.00210 -0.0782 0.7208 0.6962
0.000 0.3381 0.00727 0.00210 -0.0783 0.7135 0.7055
0.250 0.3661 0.00728 0.00214 -0.0783 0.7059 0.7136
0.500 0.3944 0.00731 0.00215 -0.0783 0.6984 0.7224
0.750 0.4225 0.00734 0.00220 -0.0783 0.6907 0.7309
1.000 0.4506 0.00738 0.00223 -0.0783 0.6830 0.7393
1.250 0.4787 0.00741 0.00228 -0.0783 0.6750 0.7482
1.500 0.5065 0.00746 0.00233 -0.0782 0.6672 0.7564
1.750 0.5347 0.00751 0.00240 -0.0783 0.6588 0.7657
2.000 0.5622 0.00757 0.00246 -0.0781 0.6510 0.7737
2.250 0.5902 0.00761 0.00255 -0.0781 0.6418 0.7829
2.500 0.6174 0.00767 0.00262 -0.0779 0.6326 0.7912
2.750 0.6448 0.00773 0.00269 -0.0778 0.6219 0.7999
3.000 0.6719 0.00778 0.00278 -0.0776 0.6100 0.8088
3.250 0.6987 0.00784 0.00287 -0.0773 0.5969 0.8172
3.500 0.7257 0.00792 0.00295 -0.0771 0.5831 0.8267
3.750 0.7512 0.00801 0.00303 -0.0765 0.5633 0.8351
4.000 0.7771 0.00813 0.00314 -0.0761 0.5434 0.8445
4.250 0.8030 0.00825 0.00328 -0.0757 0.5276 0.8539
4.500 0.8284 0.00838 0.00342 -0.0752 0.5082 0.8633
4.750 0.8533 0.00857 0.00359 -0.0746 0.4857 0.8738
5.000 0.8769 0.00879 0.00376 -0.0738 0.4524 0.8847
5.250 0.8975 0.00921 0.00399 -0.0725 0.3978 0.8967
5.500 0.9139 0.00995 0.00438 -0.0706 0.3167 0.9112
5.750 0.9267 0.01089 0.00493 -0.0682 0.2274 0.9310
6.000 0.9431 0.01183 0.00549 -0.0666 0.1482 0.9792
6.250 0.9638 0.01286 0.00615 -0.0661 0.0872 1.0000
6.500 0.9848 0.01374 0.00681 -0.0655 0.0553 1.0000
6.750 1.0072 0.01442 0.00744 -0.0649 0.0438 1.0000
7.000 1.0298 0.01503 0.00803 -0.0643 0.0375 1.0000
7.250 1.0513 0.01569 0.00872 -0.0635 0.0333 1.0000
7.500 1.0724 0.01633 0.00937 -0.0627 0.0301 1.0000
7.750 1.0890 0.01731 0.01039 -0.0612 0.0276 1.0000
8.000 1.1092 0.01794 0.01108 -0.0602 0.0261 1.0000
8.250 1.1280 0.01863 0.01181 -0.0590 0.0246 1.0000
8.500 1.1447 0.01942 0.01262 -0.0576 0.0233 1.0000
8.750 1.1501 0.02091 0.01416 -0.0545 0.0219 1.0000
9.000 1.1656 0.02160 0.01491 -0.0528 0.0215 1.0000
9.250 1.1791 0.02245 0.01584 -0.0509 0.0209 1.0000
9.500 1.1921 0.02338 0.01683 -0.0490 0.0203 1.0000
9.750 1.2046 0.02440 0.01792 -0.0472 0.0197 1.0000
10.000 1.2171 0.02547 0.01906 -0.0455 0.0192 1.0000
10.250 1.2296 0.02659 0.02024 -0.0439 0.0187 1.0000
10.500 1.2418 0.02781 0.02151 -0.0424 0.0183 1.0000
10.750 1.2536 0.02915 0.02290 -0.0410 0.0178 1.0000
11.000 1.2671 0.03130 0.02512 -0.0398 0.0173 1.0000
11.250 1.2796 0.03293 0.02689 -0.0386 0.0168 1.0000
11.500 1.2910 0.03433 0.02842 -0.0373 0.0166 1.0000
11.750 1.3017 0.03595 0.03019 -0.0360 0.0163 1.0000
12.000 1.3114 0.03780 0.03220 -0.0347 0.0160 1.0000
12.250 1.3191 0.03979 0.03436 -0.0335 0.0157 1.0000
12.500 1.3250 0.04203 0.03678 -0.0322 0.0155 1.0000
12.750 1.3285 0.04448 0.03940 -0.0310 0.0153 1.0000
13.000 1.3295 0.04713 0.04224 -0.0299 0.0151 1.0000
13.250 1.3284 0.05001 0.04531 -0.0290 0.0150 1.0000
13.500 1.3245 0.05322 0.04871 -0.0283 0.0148 1.0000
13.750 1.3201 0.05648 0.05214 -0.0280 0.0147 1.0000
14.000 1.3150 0.05988 0.05569 -0.0279 0.0145 1.0000
14.250 1.3092 0.06348 0.05944 -0.0282 0.0144 1.0000
14.500 1.3033 0.06714 0.06322 -0.0288 0.0142 1.0000
14.750 1.2931 0.07160 0.06784 -0.0299 0.0141 1.0000
15.000 1.2820 0.07645 0.07284 -0.0315 0.0140 1.0000
15.250 1.2686 0.08194 0.07850 -0.0336 0.0139 1.0000
15.500 1.2509 0.08854 0.08529 -0.0365 0.0139 1.0000
15.750 1.2277 0.09666 0.09365 -0.0407 0.0139 1.0000
16.000 1.1903 0.10844 0.10574 -0.0475 0.0141 1.0000
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