NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-66 (naca001066-il) Reynolds number: 1,000,000 Max Cl/Cd: 59.66 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001066-il-1000000-n5.txt Download as CSV file: xf-naca001066-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-66
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8461 0.13558 0.13359 -0.0264 0.9986 0.0063
-17.250 -1.2316 0.05315 0.05024 -0.0731 0.9983 0.0047
-17.000 -1.2536 0.04725 0.04414 -0.0751 0.9975 0.0047
-16.750 -1.2668 0.04330 0.04002 -0.0749 0.9968 0.0047
-16.500 -1.2755 0.04024 0.03680 -0.0737 0.9962 0.0048
-16.250 -1.2797 0.03775 0.03416 -0.0722 0.9956 0.0049
-16.000 -1.2806 0.03564 0.03191 -0.0704 0.9951 0.0050
-15.750 -1.2786 0.03380 0.02993 -0.0686 0.9947 0.0050
-15.500 -1.2765 0.03220 0.02820 -0.0662 0.9939 0.0051
-15.250 -1.2732 0.03080 0.02666 -0.0636 0.9927 0.0052
-15.000 -1.2671 0.02950 0.02522 -0.0613 0.9915 0.0053
-14.750 -1.2590 0.02831 0.02391 -0.0592 0.9904 0.0055
-14.500 -1.2490 0.02722 0.02269 -0.0572 0.9895 0.0056
-14.250 -1.2369 0.02622 0.02158 -0.0555 0.9887 0.0057
-14.000 -1.2231 0.02530 0.02054 -0.0540 0.9879 0.0058
-13.750 -1.2103 0.02418 0.01930 -0.0523 0.9873 0.0061
-13.500 -1.1948 0.02322 0.01825 -0.0510 0.9867 0.0064
-13.250 -1.1770 0.02237 0.01732 -0.0500 0.9862 0.0067
-13.000 -1.1576 0.02159 0.01644 -0.0493 0.9858 0.0070
-12.750 -1.1369 0.02087 0.01563 -0.0487 0.9854 0.0073
-12.500 -1.1306 0.02039 0.01506 -0.0447 0.9822 0.0075
-12.250 -1.1131 0.01981 0.01439 -0.0432 0.9809 0.0078
-12.000 -1.0936 0.01925 0.01375 -0.0421 0.9799 0.0080
-11.750 -1.0735 0.01859 0.01301 -0.0412 0.9790 0.0086
-11.500 -1.0517 0.01799 0.01236 -0.0406 0.9784 0.0092
-11.250 -1.0288 0.01746 0.01176 -0.0401 0.9778 0.0098
-11.000 -1.0047 0.01696 0.01120 -0.0399 0.9773 0.0105
-10.750 -0.9797 0.01648 0.01066 -0.0399 0.9769 0.0112
-10.500 -0.9541 0.01600 0.01017 -0.0400 0.9765 0.0126
-10.250 -0.9281 0.01560 0.00974 -0.0401 0.9762 0.0139
-10.000 -0.9023 0.01522 0.00932 -0.0402 0.9758 0.0149
-9.750 -0.8760 0.01487 0.00897 -0.0403 0.9755 0.0164
-9.500 -0.8711 0.01478 0.00886 -0.0354 0.9713 0.0174
-9.250 -0.8491 0.01455 0.00861 -0.0345 0.9700 0.0186
-9.000 -0.8248 0.01432 0.00835 -0.0340 0.9691 0.0196
-8.750 -0.7992 0.01411 0.00810 -0.0339 0.9683 0.0202
-8.500 -0.7735 0.01372 0.00768 -0.0338 0.9677 0.0215
-8.250 -0.7471 0.01343 0.00738 -0.0339 0.9671 0.0225
-8.000 -0.7204 0.01319 0.00713 -0.0340 0.9665 0.0236
-7.750 -0.6936 0.01295 0.00688 -0.0341 0.9660 0.0246
-7.500 -0.6668 0.01272 0.00661 -0.0342 0.9656 0.0254
-7.250 -0.6397 0.01249 0.00636 -0.0343 0.9651 0.0261
-7.000 -0.6124 0.01229 0.00613 -0.0345 0.9647 0.0266
-6.750 -0.5848 0.01210 0.00592 -0.0347 0.9643 0.0269
-6.500 -0.5743 0.01192 0.00571 -0.0309 0.9612 0.0278
-6.250 -0.5563 0.01169 0.00545 -0.0289 0.9590 0.0290
-6.000 -0.5325 0.01145 0.00518 -0.0282 0.9577 0.0300
-5.750 -0.5071 0.01122 0.00495 -0.0278 0.9567 0.0309
-5.500 -0.4812 0.01102 0.00474 -0.0276 0.9559 0.0319
-5.250 -0.4549 0.01083 0.00454 -0.0275 0.9552 0.0329
-5.000 -0.4282 0.01065 0.00435 -0.0274 0.9546 0.0337
-4.750 -0.4012 0.01048 0.00417 -0.0274 0.9540 0.0344
-4.500 -0.3740 0.01031 0.00399 -0.0275 0.9535 0.0351
-4.250 -0.3465 0.01015 0.00382 -0.0276 0.9530 0.0366
-4.000 -0.3189 0.00996 0.00367 -0.0278 0.9525 0.0402
-3.750 -0.2911 0.00979 0.00353 -0.0279 0.9521 0.0446
-3.500 -0.2633 0.00959 0.00339 -0.0282 0.9517 0.0566
-3.250 -0.2608 0.00961 0.00346 -0.0223 0.9468 0.0686
-3.000 -0.2402 0.00948 0.00340 -0.0208 0.9450 0.0844
-2.750 -0.2167 0.00934 0.00332 -0.0200 0.9438 0.0997
-2.500 -0.1922 0.00917 0.00324 -0.0194 0.9428 0.1195
-2.250 -0.1671 0.00899 0.00317 -0.0190 0.9420 0.1436
-2.000 -0.1407 0.00875 0.00306 -0.0189 0.9412 0.1769
-1.750 -0.1100 0.00836 0.00287 -0.0198 0.9401 0.2283
-1.500 -0.0762 0.00784 0.00262 -0.0214 0.9388 0.2991
-1.000 -0.0465 0.00733 0.00243 -0.0155 0.9296 0.3939
-0.750 -0.0128 0.00642 0.00195 -0.0170 0.9235 0.5186
-0.500 -0.0300 0.00585 0.00181 -0.0065 0.9131 0.6398
-0.250 -0.0421 0.00494 0.00176 0.0032 0.9050 0.8662
0.000 -0.0002 0.00492 0.00179 0.0001 0.8941 0.8942
0.250 0.0420 0.00494 0.00176 -0.0031 0.8661 0.9050
0.500 0.0296 0.00587 0.00182 0.0066 0.6379 0.9132
0.750 0.0126 0.00643 0.00195 0.0171 0.5157 0.9235
1.000 0.0466 0.00733 0.00243 0.0155 0.3944 0.9296
1.250 0.0624 0.00765 0.00256 0.0182 0.3393 0.9346
1.500 0.0763 0.00784 0.00262 0.0214 0.2990 0.9388
1.750 0.1101 0.00836 0.00287 0.0197 0.2298 0.9401
2.000 0.1408 0.00875 0.00306 0.0188 0.1768 0.9412
2.250 0.1671 0.00899 0.00317 0.0190 0.1434 0.9420
2.500 0.1922 0.00917 0.00324 0.0194 0.1197 0.9428
2.750 0.2167 0.00934 0.00332 0.0200 0.0999 0.9438
3.000 0.2403 0.00948 0.00340 0.0208 0.0845 0.9450
3.250 0.2608 0.00961 0.00346 0.0223 0.0687 0.9468
3.500 0.2634 0.00959 0.00339 0.0281 0.0568 0.9517
3.750 0.2912 0.00979 0.00353 0.0279 0.0446 0.9521
4.000 0.3189 0.00996 0.00366 0.0277 0.0403 0.9525
4.250 0.3466 0.01015 0.00382 0.0276 0.0364 0.9530
4.500 0.3741 0.01031 0.00399 0.0275 0.0351 0.9535
4.750 0.4013 0.01048 0.00417 0.0274 0.0344 0.9540
5.000 0.4283 0.01065 0.00435 0.0274 0.0337 0.9546
5.250 0.4550 0.01083 0.00454 0.0275 0.0329 0.9552
5.500 0.4813 0.01102 0.00474 0.0276 0.0319 0.9559
5.750 0.5072 0.01122 0.00495 0.0278 0.0309 0.9567
6.000 0.5325 0.01145 0.00518 0.0282 0.0300 0.9577
6.250 0.5564 0.01168 0.00544 0.0289 0.0290 0.9590
6.500 0.5744 0.01192 0.00571 0.0309 0.0278 0.9612
6.750 0.5850 0.01210 0.00592 0.0347 0.0269 0.9643
7.000 0.6126 0.01229 0.00612 0.0344 0.0266 0.9647
7.250 0.6400 0.01250 0.00637 0.0342 0.0261 0.9651
7.500 0.6671 0.01272 0.00661 0.0341 0.0254 0.9656
7.750 0.6939 0.01296 0.00688 0.0340 0.0246 0.9660
8.000 0.7206 0.01319 0.00714 0.0339 0.0236 0.9665
8.250 0.7474 0.01343 0.00738 0.0338 0.0225 0.9671
8.500 0.7738 0.01372 0.00768 0.0338 0.0215 0.9677
8.750 0.7995 0.01411 0.00810 0.0338 0.0202 0.9683
9.000 0.8251 0.01433 0.00835 0.0340 0.0196 0.9691
9.250 0.8493 0.01455 0.00861 0.0344 0.0186 0.9700
9.500 0.8712 0.01478 0.00886 0.0354 0.0174 0.9714
9.750 0.8765 0.01487 0.00896 0.0402 0.0164 0.9755
10.000 0.9027 0.01522 0.00932 0.0401 0.0149 0.9758
10.250 0.9286 0.01560 0.00974 0.0400 0.0139 0.9762
10.500 0.9546 0.01600 0.01017 0.0399 0.0126 0.9765
10.750 0.9802 0.01648 0.01066 0.0398 0.0112 0.9769
11.000 1.0052 0.01696 0.01120 0.0398 0.0105 0.9773
11.250 1.0293 0.01746 0.01176 0.0400 0.0098 0.9778
11.500 1.0523 0.01800 0.01237 0.0404 0.0092 0.9784
11.750 1.0740 0.01860 0.01302 0.0411 0.0086 0.9791
12.000 1.0942 0.01926 0.01375 0.0420 0.0080 0.9799
12.250 1.1137 0.01981 0.01439 0.0431 0.0078 0.9809
12.500 1.1311 0.02039 0.01506 0.0446 0.0075 0.9823
12.750 1.1377 0.02088 0.01563 0.0486 0.0073 0.9855
13.000 1.1584 0.02161 0.01645 0.0491 0.0070 0.9858
13.250 1.1779 0.02238 0.01733 0.0498 0.0067 0.9863
13.500 1.1957 0.02323 0.01826 0.0508 0.0064 0.9867
13.750 1.2114 0.02418 0.01931 0.0521 0.0061 0.9873
14.000 1.2242 0.02530 0.02055 0.0537 0.0058 0.9880
14.250 1.2381 0.02623 0.02159 0.0553 0.0057 0.9887
14.500 1.2502 0.02722 0.02270 0.0570 0.0056 0.9896
14.750 1.2603 0.02831 0.02391 0.0589 0.0055 0.9905
15.000 1.2682 0.02950 0.02522 0.0611 0.0053 0.9916
15.250 1.2745 0.03079 0.02665 0.0634 0.0052 0.9928
15.500 1.2776 0.03220 0.02819 0.0660 0.0051 0.9941
15.750 1.2804 0.03380 0.02993 0.0682 0.0050 0.9947
16.000 1.2824 0.03564 0.03191 0.0701 0.0049 0.9952
16.250 1.2815 0.03776 0.03417 0.0718 0.0049 0.9957
16.500 1.2772 0.04026 0.03682 0.0734 0.0048 0.9963
16.750 1.2688 0.04330 0.04002 0.0745 0.0047 0.9969
17.000 1.2556 0.04725 0.04415 0.0747 0.0047 0.9976
17.250 1.2337 0.05315 0.05025 0.0727 0.0047 0.9984
17.500 0.8466 0.13616 0.13417 0.0256 0.0063 0.9987
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