NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il) Reynolds number: 1,000,000 Max Cl/Cd: 58.98 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n0011sc-il-1000000.txt Download as CSV file: xf-n0011sc-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA/LANGLEY SYMMETRICAL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0275 0.09411 0.09149 -0.0447 1.0000 0.0178
-17.500 -1.0870 0.07856 0.07559 -0.0545 1.0000 0.0175
-17.250 -1.1184 0.06942 0.06626 -0.0600 1.0000 0.0175
-17.000 -1.1415 0.06237 0.05904 -0.0639 1.0000 0.0175
-16.750 -1.1565 0.05711 0.05363 -0.0663 1.0000 0.0174
-16.500 -1.1769 0.05179 0.04816 -0.0680 1.0000 0.0175
-16.250 -1.1907 0.04779 0.04405 -0.0684 1.0000 0.0177
-16.000 -1.2019 0.04449 0.04063 -0.0679 1.0000 0.0178
-15.750 -1.2068 0.04214 0.03821 -0.0669 1.0000 0.0179
-15.500 -1.2176 0.03938 0.03530 -0.0652 1.0000 0.0178
-15.250 -1.2216 0.03750 0.03334 -0.0631 1.0000 0.0180
-15.000 -1.2270 0.03559 0.03132 -0.0606 1.0000 0.0180
-14.750 -1.2319 0.03385 0.02946 -0.0576 1.0000 0.0180
-14.500 -1.2302 0.03281 0.02838 -0.0549 1.0000 0.0183
-14.250 -1.2306 0.03163 0.02712 -0.0518 1.0000 0.0183
-14.000 -1.2295 0.03065 0.02607 -0.0486 1.0000 0.0186
-13.750 -1.2291 0.02964 0.02498 -0.0450 1.0000 0.0187
-13.500 -1.2293 0.02861 0.02386 -0.0413 1.0000 0.0187
-13.250 -1.2293 0.02764 0.02279 -0.0372 1.0000 0.0189
-13.000 -1.2274 0.02687 0.02194 -0.0333 1.0000 0.0190
-12.750 -1.2255 0.02616 0.02115 -0.0292 1.0000 0.0192
-12.500 -1.2248 0.02536 0.02025 -0.0248 1.0000 0.0193
-12.250 -1.2236 0.02467 0.01949 -0.0203 1.0000 0.0194
-12.000 -1.2227 0.02404 0.01877 -0.0156 1.0000 0.0195
-11.750 -1.2225 0.02348 0.01814 -0.0106 1.0000 0.0196
-11.500 -1.2218 0.02300 0.01758 -0.0057 1.0000 0.0198
-11.250 -1.2029 0.02230 0.01679 -0.0045 0.9991 0.0199
-11.000 -1.1809 0.02164 0.01605 -0.0039 0.9979 0.0201
-10.750 -1.1570 0.02111 0.01545 -0.0037 0.9967 0.0203
-10.500 -1.1337 0.02034 0.01459 -0.0034 0.9955 0.0205
-10.250 -1.1121 0.01933 0.01351 -0.0029 0.9944 0.0210
-10.000 -1.0924 0.01869 0.01284 -0.0017 0.9928 0.0213
-9.750 -1.0709 0.01822 0.01234 -0.0007 0.9911 0.0217
-9.500 -1.0474 0.01773 0.01181 -0.0002 0.9895 0.0219
-9.250 -1.0215 0.01733 0.01139 -0.0001 0.9882 0.0225
-9.000 -0.9949 0.01693 0.01094 -0.0002 0.9871 0.0230
-8.750 -0.9677 0.01655 0.01052 -0.0003 0.9862 0.0234
-8.500 -0.9393 0.01626 0.01019 -0.0007 0.9855 0.0239
-8.250 -0.9122 0.01570 0.00959 -0.0009 0.9848 0.0244
-8.000 -0.8969 0.01516 0.00903 0.0015 0.9815 0.0251
-7.750 -0.8736 0.01484 0.00870 0.0023 0.9794 0.0258
-7.500 -0.8476 0.01451 0.00836 0.0025 0.9779 0.0264
-7.250 -0.8194 0.01423 0.00805 0.0023 0.9767 0.0274
-7.000 -0.7900 0.01397 0.00777 0.0018 0.9758 0.0281
-6.750 -0.7623 0.01350 0.00730 0.0016 0.9749 0.0296
-6.500 -0.7320 0.01325 0.00705 0.0009 0.9743 0.0309
-6.250 -0.7007 0.01304 0.00683 0.0000 0.9737 0.0323
-6.000 -0.6889 0.01271 0.00650 0.0035 0.9690 0.0338
-5.750 -0.6631 0.01246 0.00627 0.0039 0.9669 0.0357
-5.500 -0.6344 0.01226 0.00606 0.0036 0.9655 0.0375
-5.250 -0.6054 0.01195 0.00578 0.0033 0.9643 0.0407
-5.000 -0.5745 0.01175 0.00558 0.0026 0.9634 0.0434
-4.750 -0.5438 0.01146 0.00534 0.0019 0.9626 0.0482
-4.500 -0.5122 0.01121 0.00513 0.0010 0.9619 0.0535
-4.250 -0.4800 0.01097 0.00494 -0.0001 0.9613 0.0609
-4.000 -0.4680 0.01081 0.00480 0.0035 0.9557 0.0663
-3.750 -0.4406 0.01056 0.00462 0.0036 0.9536 0.0777
-3.500 -0.4113 0.01028 0.00444 0.0032 0.9520 0.0936
-3.250 -0.3803 0.00999 0.00425 0.0025 0.9508 0.1133
-3.000 -0.3487 0.00967 0.00407 0.0016 0.9499 0.1411
-2.750 -0.3162 0.00932 0.00388 0.0005 0.9490 0.1768
-2.500 -0.2836 0.00892 0.00369 -0.0007 0.9483 0.2231
-2.250 -0.2510 0.00845 0.00348 -0.0019 0.9477 0.2851
-2.000 -0.2456 0.00816 0.00339 0.0032 0.9400 0.3398
-1.750 -0.2199 0.00753 0.00315 0.0035 0.9379 0.4390
-1.500 -0.1945 0.00666 0.00280 0.0040 0.9360 0.5746
-1.250 -0.1657 0.00564 0.00233 0.0041 0.9336 0.7149
-1.000 -0.1631 0.00520 0.00216 0.0103 0.9236 0.7847
-0.750 -0.1194 0.00485 0.00204 0.0071 0.9205 0.8467
-0.500 -0.0646 0.00473 0.00200 0.0013 0.9183 0.8744
-0.250 -0.0449 0.00472 0.00202 0.0036 0.9088 0.8898
0.000 0.0018 0.00465 0.00194 -0.0004 0.9022 0.9026
0.250 0.0438 0.00473 0.00204 -0.0033 0.8905 0.9092
0.500 0.0662 0.00473 0.00199 -0.0017 0.8734 0.9183
0.750 0.1204 0.00486 0.00204 -0.0073 0.8436 0.9206
1.000 0.1627 0.00520 0.00215 -0.0102 0.7844 0.9235
1.250 0.1654 0.00565 0.00233 -0.0040 0.7116 0.9336
1.500 0.1954 0.00661 0.00279 -0.0042 0.5832 0.9359
1.750 0.2200 0.00755 0.00316 -0.0036 0.4370 0.9379
2.000 0.2451 0.00817 0.00339 -0.0031 0.3370 0.9400
2.250 0.2512 0.00843 0.00347 0.0018 0.2887 0.9477
2.500 0.2839 0.00890 0.00369 0.0006 0.2265 0.9483
2.750 0.3163 0.00932 0.00388 -0.0005 0.1767 0.9491
3.000 0.3486 0.00967 0.00407 -0.0016 0.1410 0.9499
3.250 0.3803 0.00999 0.00425 -0.0025 0.1137 0.9508
3.500 0.4111 0.01029 0.00443 -0.0032 0.0923 0.9520
3.750 0.4405 0.01057 0.00462 -0.0036 0.0770 0.9536
4.000 0.4680 0.01081 0.00480 -0.0035 0.0664 0.9557
4.250 0.4799 0.01098 0.00494 0.0001 0.0599 0.9613
4.500 0.5122 0.01122 0.00513 -0.0010 0.0532 0.9619
4.750 0.5438 0.01146 0.00534 -0.0019 0.0476 0.9626
5.000 0.5745 0.01175 0.00558 -0.0026 0.0434 0.9634
5.250 0.6056 0.01194 0.00577 -0.0033 0.0407 0.9644
5.500 0.6344 0.01226 0.00606 -0.0036 0.0375 0.9655
5.750 0.6631 0.01247 0.00627 -0.0039 0.0357 0.9670
6.000 0.6886 0.01273 0.00651 -0.0035 0.0337 0.9691
6.250 0.7009 0.01303 0.00682 -0.0001 0.0322 0.9737
6.500 0.7322 0.01323 0.00703 -0.0010 0.0308 0.9743
6.750 0.7623 0.01351 0.00730 -0.0016 0.0293 0.9749
7.000 0.7903 0.01396 0.00775 -0.0019 0.0279 0.9758
7.250 0.8198 0.01420 0.00802 -0.0024 0.0270 0.9767
7.500 0.8477 0.01452 0.00836 -0.0025 0.0262 0.9780
7.750 0.8739 0.01482 0.00868 -0.0024 0.0256 0.9795
8.000 0.8965 0.01520 0.00906 -0.0015 0.0249 0.9815
8.250 0.9116 0.01580 0.00968 0.0010 0.0242 0.9848
8.500 0.9394 0.01627 0.01021 0.0007 0.0238 0.9855
8.750 0.9678 0.01657 0.01055 0.0003 0.0233 0.9862
9.000 0.9945 0.01699 0.01101 0.0002 0.0230 0.9871
9.250 1.0213 0.01736 0.01142 0.0001 0.0225 0.9882
9.500 1.0474 0.01777 0.01185 0.0002 0.0220 0.9896
9.750 1.0711 0.01823 0.01235 0.0007 0.0217 0.9912
10.000 1.0924 0.01872 0.01287 0.0016 0.0213 0.9929
10.250 1.1126 0.01932 0.01351 0.0027 0.0210 0.9945
10.500 1.1354 0.02022 0.01447 0.0031 0.0207 0.9955
10.750 1.1570 0.02121 0.01556 0.0036 0.0203 0.9967
11.000 1.1807 0.02175 0.01617 0.0039 0.0201 0.9980
11.250 1.2025 0.02244 0.01694 0.0045 0.0200 0.9992
11.500 1.2217 0.02302 0.01760 0.0057 0.0198 1.0000
11.750 1.2223 0.02353 0.01819 0.0107 0.0196 1.0000
12.000 1.2222 0.02413 0.01887 0.0157 0.0196 1.0000
12.250 1.2227 0.02479 0.01961 0.0204 0.0195 1.0000
12.500 1.2252 0.02532 0.02022 0.0247 0.0192 1.0000
12.750 1.2258 0.02614 0.02113 0.0292 0.0192 1.0000
13.000 1.2284 0.02680 0.02186 0.0332 0.0190 1.0000
13.250 1.2281 0.02777 0.02293 0.0374 0.0189 1.0000
13.500 1.2286 0.02871 0.02397 0.0413 0.0188 1.0000
13.750 1.2304 0.02954 0.02487 0.0449 0.0186 1.0000
14.000 1.2311 0.03052 0.02593 0.0484 0.0185 1.0000
14.250 1.2284 0.03187 0.02738 0.0520 0.0185 1.0000
14.500 1.2316 0.03271 0.02828 0.0548 0.0182 1.0000
14.750 1.2228 0.03473 0.03045 0.0584 0.0183 1.0000
15.000 1.2242 0.03590 0.03167 0.0607 0.0181 1.0000
15.250 1.2225 0.03746 0.03330 0.0630 0.0180 1.0000
15.500 1.2175 0.03945 0.03538 0.0651 0.0179 1.0000
15.750 1.2095 0.04191 0.03795 0.0668 0.0178 1.0000
16.000 1.1980 0.04499 0.04119 0.0679 0.0179 1.0000
16.250 1.1882 0.04818 0.04446 0.0682 0.0177 1.0000
16.500 1.1752 0.05214 0.04856 0.0677 0.0177 1.0000
16.750 1.1595 0.05693 0.05350 0.0662 0.0177 1.0000
17.000 1.1434 0.06227 0.05896 0.0637 0.0176 1.0000
17.250 1.1208 0.06932 0.06618 0.0598 0.0176 1.0000
17.500 1.0857 0.07929 0.07638 0.0536 0.0177 1.0000
17.750 1.0520 0.08936 0.08661 0.0476 0.0176 1.0000
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