NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0012 AIRFOILS (n0012-il) Reynolds number: 200,000 Max Cl/Cd: 47.43 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0012-il-200000.txt Download as CSV file: xf-n0012-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012 AIRFOILS
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9628 0.07963 0.07518 -0.0278 1.0000 0.0399
-13.750 -0.9895 0.07225 0.06762 -0.0322 1.0000 0.0398
-13.500 -1.0148 0.06593 0.06110 -0.0354 1.0000 0.0397
-13.250 -1.0382 0.06063 0.05557 -0.0371 1.0000 0.0396
-13.000 -1.0594 0.05622 0.05090 -0.0373 1.0000 0.0396
-12.750 -1.0784 0.05255 0.04697 -0.0361 1.0000 0.0397
-12.500 -1.0955 0.04958 0.04371 -0.0335 1.0000 0.0399
-12.000 -1.1063 0.04365 0.03734 -0.0286 1.0000 0.0410
-11.750 -1.0964 0.04195 0.03559 -0.0273 1.0000 0.0420
-11.500 -1.0857 0.04034 0.03389 -0.0259 1.0000 0.0430
-11.250 -1.0770 0.03842 0.03176 -0.0241 1.0000 0.0441
-11.000 -1.0679 0.03635 0.02942 -0.0222 1.0000 0.0451
-10.750 -1.0569 0.03444 0.02717 -0.0203 1.0000 0.0462
-10.500 -1.0443 0.03262 0.02503 -0.0186 1.0000 0.0474
-10.250 -1.0249 0.03076 0.02323 -0.0180 1.0000 0.0492
-10.000 -1.0066 0.02966 0.02206 -0.0169 1.0000 0.0511
-9.750 -0.9881 0.02844 0.02068 -0.0156 1.0000 0.0532
-9.500 -0.9692 0.02734 0.01932 -0.0143 1.0000 0.0550
-9.250 -0.9491 0.02559 0.01762 -0.0135 1.0000 0.0576
-9.000 -0.9290 0.02473 0.01674 -0.0124 1.0000 0.0604
-8.750 -0.9087 0.02387 0.01574 -0.0112 1.0000 0.0635
-8.500 -0.8890 0.02252 0.01438 -0.0101 1.0000 0.0667
-8.250 -0.8689 0.02174 0.01362 -0.0089 1.0000 0.0707
-8.000 -0.8481 0.02113 0.01286 -0.0077 1.0000 0.0749
-7.750 -0.8300 0.01996 0.01181 -0.0062 1.0000 0.0799
-7.500 -0.8096 0.01936 0.01114 -0.0049 1.0000 0.0858
-7.250 -0.7919 0.01844 0.01031 -0.0033 1.0000 0.0925
-7.000 -0.7726 0.01776 0.00961 -0.0018 1.0000 0.1005
-6.750 -0.7535 0.01712 0.00900 -0.0003 1.0000 0.1104
-6.500 -0.7351 0.01641 0.00837 0.0013 1.0000 0.1222
-6.250 -0.7162 0.01577 0.00781 0.0028 1.0000 0.1373
-6.000 -0.6971 0.01517 0.00729 0.0043 1.0000 0.1563
-5.750 -0.6785 0.01455 0.00683 0.0058 1.0000 0.1796
-5.500 -0.6592 0.01400 0.00643 0.0073 1.0000 0.2077
-5.250 -0.6396 0.01350 0.00609 0.0086 1.0000 0.2398
-5.000 -0.6195 0.01306 0.00580 0.0099 1.0000 0.2743
-4.750 -0.5990 0.01268 0.00556 0.0111 1.0000 0.3101
-4.500 -0.5783 0.01234 0.00537 0.0123 1.0000 0.3456
-4.250 -0.5572 0.01203 0.00521 0.0134 1.0000 0.3809
-4.000 -0.5358 0.01176 0.00508 0.0145 1.0000 0.4160
-3.750 -0.5139 0.01154 0.00498 0.0155 1.0000 0.4509
-3.500 -0.4915 0.01134 0.00492 0.0164 1.0000 0.4856
-3.250 -0.4689 0.01118 0.00489 0.0172 1.0000 0.5202
-3.000 -0.4463 0.01104 0.00489 0.0180 1.0000 0.5545
-2.750 -0.4236 0.01094 0.00493 0.0188 1.0000 0.5885
-2.500 -0.3942 0.01086 0.00497 0.0183 0.9979 0.6248
-2.250 -0.3513 0.01075 0.00504 0.0152 0.9915 0.6638
-2.000 -0.3085 0.01066 0.00509 0.0122 0.9843 0.7011
-1.750 -0.2684 0.01056 0.00512 0.0100 0.9755 0.7357
-1.500 -0.2255 0.01048 0.00517 0.0072 0.9686 0.7684
-1.250 -0.1861 0.01040 0.00519 0.0054 0.9593 0.7978
-1.000 -0.1454 0.01034 0.00519 0.0033 0.9509 0.8255
-0.750 -0.1048 0.01028 0.00521 0.0015 0.9424 0.8482
-0.500 -0.0700 0.01025 0.00522 0.0009 0.9304 0.8696
-0.250 -0.0350 0.01022 0.00521 0.0004 0.9182 0.8886
0.000 0.0000 0.01020 0.00520 0.0000 0.9046 0.9047
0.250 0.0350 0.01022 0.00521 -0.0004 0.8886 0.9182
0.500 0.0700 0.01025 0.00522 -0.0009 0.8696 0.9304
0.750 0.1048 0.01028 0.00521 -0.0015 0.8482 0.9424
1.000 0.1454 0.01034 0.00519 -0.0033 0.8255 0.9510
1.250 0.1861 0.01040 0.00518 -0.0054 0.7978 0.9593
1.500 0.2255 0.01048 0.00517 -0.0072 0.7684 0.9686
1.750 0.2684 0.01056 0.00512 -0.0100 0.7357 0.9756
2.000 0.3085 0.01066 0.00509 -0.0122 0.7012 0.9843
2.250 0.3513 0.01075 0.00504 -0.0152 0.6637 0.9915
2.500 0.3942 0.01085 0.00497 -0.0183 0.6249 0.9979
2.750 0.4235 0.01094 0.00492 -0.0188 0.5886 1.0000
3.000 0.4462 0.01104 0.00489 -0.0180 0.5545 1.0000
3.250 0.4689 0.01118 0.00489 -0.0172 0.5202 1.0000
3.500 0.4915 0.01134 0.00492 -0.0163 0.4857 1.0000
3.750 0.5138 0.01153 0.00498 -0.0155 0.4509 1.0000
4.000 0.5357 0.01176 0.00507 -0.0145 0.4160 1.0000
4.250 0.5571 0.01203 0.00521 -0.0134 0.3810 1.0000
4.500 0.5782 0.01234 0.00536 -0.0123 0.3456 1.0000
4.750 0.5990 0.01268 0.00556 -0.0111 0.3101 1.0000
5.000 0.6195 0.01306 0.00580 -0.0099 0.2744 1.0000
5.250 0.6395 0.01350 0.00609 -0.0086 0.2398 1.0000
5.500 0.6591 0.01400 0.00643 -0.0072 0.2077 1.0000
5.750 0.6784 0.01455 0.00683 -0.0058 0.1796 1.0000
6.000 0.6971 0.01516 0.00729 -0.0043 0.1563 1.0000
6.250 0.7161 0.01577 0.00781 -0.0028 0.1374 1.0000
6.500 0.7351 0.01641 0.00837 -0.0013 0.1223 1.0000
6.750 0.7535 0.01712 0.00900 0.0003 0.1104 1.0000
7.000 0.7725 0.01776 0.00961 0.0018 0.1005 1.0000
7.250 0.7919 0.01844 0.01031 0.0033 0.0925 1.0000
7.500 0.8096 0.01936 0.01114 0.0049 0.0858 1.0000
7.750 0.8300 0.01995 0.01181 0.0062 0.0799 1.0000
8.000 0.8481 0.02112 0.01285 0.0077 0.0749 1.0000
8.250 0.8690 0.02173 0.01362 0.0089 0.0707 1.0000
8.500 0.8890 0.02251 0.01438 0.0101 0.0667 1.0000
8.750 0.9087 0.02387 0.01574 0.0112 0.0635 1.0000
9.000 0.9291 0.02472 0.01674 0.0124 0.0604 1.0000
9.250 0.9492 0.02559 0.01762 0.0135 0.0575 1.0000
9.500 0.9693 0.02734 0.01932 0.0143 0.0550 1.0000
9.750 0.9882 0.02844 0.02068 0.0156 0.0532 1.0000
10.000 1.0067 0.02966 0.02206 0.0168 0.0511 1.0000
10.250 1.0251 0.03077 0.02323 0.0179 0.0492 1.0000
10.500 1.0445 0.03262 0.02503 0.0185 0.0474 1.0000
10.750 1.0571 0.03445 0.02718 0.0203 0.0462 1.0000
11.000 1.0681 0.03636 0.02942 0.0222 0.0451 1.0000
11.250 1.0773 0.03842 0.03177 0.0241 0.0441 1.0000
11.500 1.0860 0.04035 0.03390 0.0258 0.0430 1.0000
11.750 1.0969 0.04194 0.03558 0.0272 0.0419 1.0000
12.000 1.1068 0.04366 0.03735 0.0286 0.0410 1.0000
12.250 1.1101 0.04727 0.04108 0.0298 0.0401 1.0000
12.500 1.0959 0.04960 0.04372 0.0334 0.0399 1.0000
12.750 1.0790 0.05258 0.04700 0.0360 0.0397 1.0000
13.000 1.0599 0.05626 0.05095 0.0372 0.0396 1.0000
13.250 1.0385 0.06069 0.05564 0.0369 0.0396 1.0000
13.500 1.0150 0.06603 0.06120 0.0352 0.0396 1.0000
13.750 0.9898 0.07237 0.06774 0.0319 0.0398 1.0000
14.000 0.9632 0.07976 0.07532 0.0275 0.0399 1.0000
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