NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il) Reynolds number: 500,000 Max Cl/Cd: 53.69 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20012-il-500000.txt Download as CSV file: xf-sc20012-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0012 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
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0628 0.09915 0.09601 -0.0086 1.0000 0.0225
-16.250 -1.1008 0.08685 0.08347 -0.0170 1.0000 0.0224
-16.000 -1.1327 0.07699 0.07339 -0.0233 1.0000 0.0223
-15.750 -1.1585 0.06922 0.06540 -0.0278 1.0000 0.0223
-15.500 -1.1795 0.06293 0.05890 -0.0307 1.0000 0.0223
-15.250 -1.1965 0.05770 0.05346 -0.0325 1.0000 0.0223
-15.000 -1.2100 0.05329 0.04884 -0.0335 1.0000 0.0224
-14.750 -1.2201 0.04951 0.04487 -0.0338 1.0000 0.0224
-14.500 -1.2297 0.04592 0.04107 -0.0335 1.0000 0.0225
-14.250 -1.2378 0.04248 0.03744 -0.0327 1.0000 0.0227
-14.000 -1.2406 0.03969 0.03451 -0.0316 1.0000 0.0228
-13.750 -1.2390 0.03750 0.03219 -0.0304 1.0000 0.0230
-13.500 -1.2346 0.03567 0.03027 -0.0291 1.0000 0.0232
-13.250 -1.2285 0.03407 0.02858 -0.0277 1.0000 0.0235
-13.000 -1.2212 0.03263 0.02705 -0.0261 1.0000 0.0237
-12.750 -1.2129 0.03131 0.02563 -0.0245 1.0000 0.0240
-12.500 -1.2039 0.03007 0.02428 -0.0226 1.0000 0.0243
-12.250 -1.1941 0.02891 0.02301 -0.0206 1.0000 0.0246
-12.000 -1.1833 0.02781 0.02180 -0.0186 1.0000 0.0250
-11.750 -1.1697 0.02674 0.02061 -0.0170 1.0000 0.0254
-11.500 -1.1539 0.02574 0.01949 -0.0156 1.0000 0.0259
-11.250 -1.1367 0.02485 0.01846 -0.0144 1.0000 0.0263
-11.000 -1.1214 0.02350 0.01705 -0.0130 1.0000 0.0269
-10.750 -1.1033 0.02264 0.01617 -0.0119 1.0000 0.0275
-10.500 -1.0832 0.02200 0.01551 -0.0110 1.0000 0.0283
-10.250 -1.0624 0.02137 0.01483 -0.0101 1.0000 0.0292
-10.000 -1.0411 0.02074 0.01411 -0.0093 1.0000 0.0302
-9.750 -1.0209 0.01989 0.01319 -0.0083 1.0000 0.0312
-9.500 -1.0002 0.01917 0.01249 -0.0075 1.0000 0.0323
-9.250 -0.9775 0.01868 0.01197 -0.0068 1.0000 0.0337
-9.000 -0.9542 0.01821 0.01143 -0.0062 1.0000 0.0353
-8.750 -0.9331 0.01746 0.01068 -0.0053 1.0000 0.0370
-8.500 -0.9094 0.01707 0.01029 -0.0048 1.0000 0.0389
-8.250 -0.8850 0.01673 0.00990 -0.0043 1.0000 0.0409
-8.000 -0.8633 0.01608 0.00927 -0.0035 1.0000 0.0431
-7.750 -0.8392 0.01576 0.00896 -0.0030 1.0000 0.0453
-7.500 -0.8146 0.01553 0.00867 -0.0024 1.0000 0.0475
-7.250 -0.7939 0.01492 0.00810 -0.0014 1.0000 0.0500
-7.000 -0.7719 0.01463 0.00783 -0.0005 1.0000 0.0524
-6.750 -0.7515 0.01440 0.00758 0.0009 1.0000 0.0545
-6.500 -0.7187 0.01377 0.00697 -0.0007 0.9957 0.0576
-6.250 -0.6823 0.01337 0.00658 -0.0028 0.9896 0.0608
-5.750 -0.6130 0.01254 0.00577 -0.0062 0.9706 0.0686
-5.500 -0.5815 0.01227 0.00548 -0.0071 0.9567 0.0724
-5.250 -0.5550 0.01188 0.00508 -0.0068 0.9403 0.0769
-5.000 -0.5301 0.01162 0.00481 -0.0062 0.9244 0.0815
-4.750 -0.5054 0.01134 0.00451 -0.0055 0.9106 0.0873
-4.500 -0.4804 0.01110 0.00425 -0.0048 0.8991 0.0955
-4.250 -0.4549 0.01079 0.00399 -0.0044 0.8884 0.1089
-4.000 -0.4298 0.01044 0.00372 -0.0039 0.8800 0.1320
-3.750 -0.4042 0.01003 0.00349 -0.0036 0.8719 0.1703
-3.500 -0.3795 0.00956 0.00325 -0.0032 0.8652 0.2284
-3.250 -0.3549 0.00897 0.00301 -0.0029 0.8585 0.3117
-3.000 -0.3317 0.00820 0.00273 -0.0025 0.8519 0.4329
-2.750 -0.3098 0.00743 0.00256 -0.0015 0.8464 0.5781
-2.500 -0.2832 0.00731 0.00265 -0.0011 0.8415 0.6498
-2.250 -0.2546 0.00732 0.00267 -0.0011 0.8370 0.6781
-2.000 -0.2261 0.00733 0.00268 -0.0011 0.8325 0.6962
-1.750 -0.1977 0.00736 0.00270 -0.0010 0.8283 0.7100
-1.500 -0.1692 0.00738 0.00272 -0.0010 0.8242 0.7217
-1.250 -0.1404 0.00739 0.00273 -0.0010 0.8190 0.7336
-1.000 -0.1124 0.00739 0.00274 -0.0008 0.8121 0.7442
-0.750 -0.0846 0.00743 0.00277 -0.0005 0.8053 0.7560
-0.500 -0.0563 0.00745 0.00280 -0.0004 0.7983 0.7679
-0.250 -0.0284 0.00743 0.00278 -0.0001 0.7910 0.7757
0.000 0.0000 0.00745 0.00280 0.0000 0.7837 0.7837
0.250 0.0284 0.00743 0.00278 0.0001 0.7755 0.7910
0.500 0.0563 0.00745 0.00280 0.0004 0.7678 0.7983
0.750 0.0846 0.00743 0.00277 0.0005 0.7563 0.8054
1.000 0.1123 0.00739 0.00274 0.0008 0.7443 0.8123
1.250 0.1403 0.00739 0.00273 0.0011 0.7335 0.8191
1.500 0.1692 0.00738 0.00272 0.0010 0.7218 0.8242
1.750 0.1977 0.00736 0.00270 0.0010 0.7100 0.8283
2.000 0.2261 0.00733 0.00268 0.0011 0.6963 0.8325
2.250 0.2546 0.00732 0.00267 0.0011 0.6781 0.8370
2.500 0.2832 0.00731 0.00265 0.0011 0.6499 0.8415
2.750 0.3098 0.00744 0.00256 0.0015 0.5776 0.8464
3.000 0.3317 0.00820 0.00273 0.0025 0.4332 0.8519
3.250 0.3548 0.00898 0.00301 0.0029 0.3111 0.8585
3.500 0.3795 0.00956 0.00325 0.0032 0.2283 0.8651
3.750 0.4042 0.01003 0.00349 0.0036 0.1702 0.8719
4.000 0.4298 0.01044 0.00372 0.0039 0.1319 0.8800
4.250 0.4549 0.01079 0.00399 0.0044 0.1088 0.8884
4.500 0.4804 0.01110 0.00425 0.0048 0.0955 0.8991
4.750 0.5054 0.01134 0.00450 0.0055 0.0874 0.9106
5.000 0.5301 0.01162 0.00481 0.0062 0.0815 0.9244
5.250 0.5550 0.01187 0.00508 0.0068 0.0768 0.9403
5.500 0.5816 0.01227 0.00548 0.0071 0.0724 0.9567
5.750 0.6131 0.01254 0.00577 0.0062 0.0686 0.9706
6.000 0.6454 0.01311 0.00628 0.0049 0.0638 0.9822
6.250 0.6824 0.01337 0.00658 0.0028 0.0608 0.9896
6.500 0.7188 0.01377 0.00696 0.0007 0.0575 0.9957
6.750 0.7514 0.01440 0.00758 -0.0008 0.0545 1.0000
7.000 0.7718 0.01463 0.00783 0.0005 0.0524 1.0000
7.250 0.7939 0.01491 0.00810 0.0014 0.0500 1.0000
7.500 0.8147 0.01553 0.00867 0.0024 0.0475 1.0000
7.750 0.8393 0.01576 0.00896 0.0030 0.0453 1.0000
8.000 0.8633 0.01608 0.00927 0.0035 0.0431 1.0000
8.250 0.8851 0.01673 0.00990 0.0043 0.0409 1.0000
8.500 0.9095 0.01707 0.01029 0.0048 0.0388 1.0000
8.750 0.9332 0.01746 0.01068 0.0053 0.0370 1.0000
9.000 0.9543 0.01821 0.01143 0.0062 0.0353 1.0000
9.250 0.9776 0.01867 0.01197 0.0068 0.0337 1.0000
9.500 1.0003 0.01917 0.01249 0.0074 0.0323 1.0000
9.750 1.0211 0.01989 0.01319 0.0083 0.0312 1.0000
10.000 1.0412 0.02074 0.01410 0.0093 0.0302 1.0000
10.250 1.0626 0.02137 0.01483 0.0101 0.0292 1.0000
10.500 1.0834 0.02200 0.01551 0.0109 0.0283 1.0000
10.750 1.1035 0.02264 0.01617 0.0118 0.0275 1.0000
11.000 1.1217 0.02350 0.01705 0.0129 0.0269 1.0000
11.250 1.1370 0.02484 0.01845 0.0143 0.0263 1.0000
11.500 1.1543 0.02574 0.01948 0.0155 0.0259 1.0000
11.750 1.1700 0.02675 0.02062 0.0169 0.0254 1.0000
12.000 1.1837 0.02781 0.02180 0.0185 0.0250 1.0000
12.250 1.1946 0.02891 0.02301 0.0205 0.0246 1.0000
12.500 1.2044 0.03008 0.02429 0.0225 0.0243 1.0000
12.750 1.2136 0.03130 0.02562 0.0243 0.0240 1.0000
13.000 1.2219 0.03263 0.02704 0.0260 0.0237 1.0000
13.250 1.2293 0.03406 0.02857 0.0276 0.0235 1.0000
13.500 1.2354 0.03565 0.03025 0.0290 0.0232 1.0000
13.750 1.2398 0.03750 0.03219 0.0303 0.0230 1.0000
14.000 1.2414 0.03971 0.03452 0.0314 0.0228 1.0000
14.250 1.2387 0.04247 0.03744 0.0325 0.0227 1.0000
14.500 1.2304 0.04596 0.04111 0.0333 0.0225 1.0000
14.750 1.2211 0.04952 0.04487 0.0336 0.0224 1.0000
15.000 1.2111 0.05329 0.04885 0.0333 0.0224 1.0000
15.250 1.1977 0.05770 0.05346 0.0323 0.0223 1.0000
15.500 1.1807 0.06295 0.05892 0.0305 0.0223 1.0000
15.750 1.1596 0.06926 0.06544 0.0275 0.0223 1.0000
16.000 1.1338 0.07707 0.07347 0.0230 0.0223 1.0000
16.250 1.1018 0.08699 0.08362 0.0166 0.0224 1.0000
16.500 1.0632 0.09944 0.09630 0.0081 0.0225 1.0000
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Polar data table (+)
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