NACA 63(3)-018 (naca633018-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(3)-018 (naca633018-il) Reynolds number: 50,000 Max Cl/Cd: 23.42 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633018-il-50000.txt Download as CSV file: xf-naca633018-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.8204 0.08389 0.07649 -0.0291 1.0000 0.1820
-12.750 -0.8748 0.07396 0.06645 -0.0328 1.0000 0.1801
-12.500 -0.9228 0.06660 0.05891 -0.0344 1.0000 0.1786
-12.250 -0.9587 0.06129 0.05336 -0.0341 1.0000 0.1783
-12.000 -0.9838 0.05723 0.04905 -0.0328 1.0000 0.1792
-11.750 -1.0026 0.05389 0.04543 -0.0306 1.0000 0.1806
-11.500 -1.0171 0.05095 0.04214 -0.0280 1.0000 0.1825
-11.250 -0.9778 0.04847 0.03978 -0.0294 1.0000 0.1914
-11.000 -0.9815 0.04601 0.03703 -0.0274 1.0000 0.1968
-10.750 -0.9485 0.04384 0.03498 -0.0281 1.0000 0.2081
-10.500 -0.9214 0.04170 0.03285 -0.0284 1.0000 0.2207
-10.250 -0.8992 0.03990 0.03114 -0.0280 1.0000 0.2375
-10.000 -0.8849 0.03814 0.02950 -0.0268 1.0000 0.2580
-9.750 -0.8632 0.03689 0.02864 -0.0257 1.0000 0.2883
-9.500 -0.8415 0.03686 0.02917 -0.0235 1.0000 0.3299
-9.250 -0.7748 0.04244 0.03513 -0.0206 1.0000 0.3889
-9.000 -0.5503 0.06748 0.05951 -0.0119 1.0000 0.4259
-8.750 -0.5481 0.06614 0.05813 -0.0107 1.0000 0.4502
-8.500 -0.4752 0.07051 0.06225 -0.0086 1.0000 0.4753
-8.250 -0.4743 0.06890 0.06063 -0.0076 1.0000 0.4971
-8.000 -0.4169 0.07034 0.06189 -0.0072 1.0000 0.5202
-7.750 -0.3943 0.06965 0.06112 -0.0068 1.0000 0.5413
-7.500 -0.3849 0.06855 0.06000 -0.0060 1.0000 0.5610
-7.250 -0.3456 0.06827 0.05962 -0.0063 1.0000 0.5833
-7.000 -0.3209 0.06764 0.05894 -0.0060 1.0000 0.6039
-6.750 -0.3104 0.06709 0.05839 -0.0046 1.0000 0.6222
-6.500 -0.3107 0.06687 0.05819 -0.0016 1.0000 0.6370
-6.250 -0.3496 0.06672 0.05813 0.0047 1.0000 0.6425
-6.000 -0.3438 0.06651 0.05789 0.0072 1.0000 0.6568
-5.750 -0.3418 0.06620 0.05757 0.0099 1.0000 0.6704
-5.500 -0.3772 0.06563 0.05704 0.0156 1.0000 0.6761
-5.250 -0.3634 0.06518 0.05654 0.0168 1.0000 0.6902
-5.000 -0.3564 0.06464 0.05597 0.0185 1.0000 0.7029
-4.750 -0.3841 0.06386 0.05520 0.0235 1.0000 0.7089
-4.500 -0.3551 0.06312 0.05438 0.0217 0.9972 0.7233
-4.250 -0.3094 0.06208 0.05320 0.0165 0.9890 0.7396
-4.000 -0.2618 0.06099 0.05199 0.0108 0.9811 0.7552
-3.750 -0.2235 0.05997 0.05087 0.0066 0.9727 0.7687
-3.500 -0.2060 0.05906 0.04988 0.0045 0.9644 0.7756
-3.250 -0.1580 0.05807 0.04879 -0.0010 0.9563 0.7891
-3.000 -0.1534 0.05746 0.04813 -0.0007 0.9477 0.7930
-2.750 -0.0980 0.05645 0.04704 -0.0073 0.9402 0.8055
-2.500 -0.0981 0.05606 0.04662 -0.0058 0.9316 0.8085
-2.250 -0.0463 0.05519 0.04569 -0.0120 0.9245 0.8191
-2.000 -0.0484 0.05497 0.04545 -0.0097 0.9159 0.8218
-1.750 -0.0424 0.05473 0.04517 -0.0090 0.9088 0.8263
-1.500 -0.0227 0.05435 0.04479 -0.0097 0.9009 0.8323
-1.250 -0.0023 0.05406 0.04447 -0.0109 0.8939 0.8376
-1.000 -0.0199 0.05412 0.04453 -0.0060 0.8870 0.8410
-0.750 -0.0124 0.05395 0.04435 -0.0049 0.8802 0.8461
-0.500 0.0162 0.05383 0.04422 -0.0072 0.8739 0.8522
-0.250 -0.0126 0.05389 0.04428 -0.0003 0.8681 0.8563
0.000 -0.0003 0.05383 0.04421 0.0001 0.8622 0.8621
0.250 0.0123 0.05389 0.04427 0.0003 0.8563 0.8680
0.500 -0.0160 0.05383 0.04421 0.0071 0.8523 0.8738
0.750 0.0110 0.05394 0.04434 0.0051 0.8462 0.8801
1.000 0.0199 0.05411 0.04452 0.0059 0.8410 0.8871
1.250 0.0023 0.05405 0.04447 0.0109 0.8377 0.8939
1.500 0.0230 0.05434 0.04477 0.0097 0.8322 0.9009
1.750 0.0417 0.05470 0.04514 0.0091 0.8262 0.9088
2.000 0.0489 0.05497 0.04545 0.0096 0.8221 0.9160
2.250 0.0459 0.05516 0.04566 0.0120 0.8191 0.9245
2.500 0.0984 0.05604 0.04660 0.0057 0.8086 0.9316
2.750 0.0980 0.05642 0.04701 0.0073 0.8055 0.9402
3.000 0.1546 0.05745 0.04812 0.0005 0.7933 0.9477
3.250 0.1582 0.05803 0.04876 0.0009 0.7890 0.9563
3.500 0.2068 0.05905 0.04986 -0.0046 0.7758 0.9644
3.750 0.2243 0.05993 0.05083 -0.0067 0.7686 0.9727
4.000 0.2620 0.06096 0.05195 -0.0108 0.7554 0.9811
4.250 0.3099 0.06204 0.05316 -0.0166 0.7396 0.9890
4.500 0.3561 0.06309 0.05434 -0.0219 0.7232 0.9974
4.750 0.3841 0.06381 0.05515 -0.0235 0.7089 1.0000
5.000 0.3565 0.06459 0.05592 -0.0185 0.7030 1.0000
5.250 0.3635 0.06513 0.05649 -0.0168 0.6902 1.0000
5.500 0.3772 0.06557 0.05697 -0.0156 0.6761 1.0000
5.750 0.3421 0.06612 0.05749 -0.0099 0.6701 1.0000
6.000 0.3438 0.06643 0.05781 -0.0072 0.6567 1.0000
6.250 0.3485 0.06663 0.05804 -0.0046 0.6423 1.0000
6.500 0.3107 0.06679 0.05811 0.0016 0.6368 1.0000
6.750 0.3105 0.06704 0.05834 0.0046 0.6222 1.0000
7.000 0.3211 0.06761 0.05891 0.0060 0.6040 1.0000
7.250 0.3490 0.06816 0.05951 0.0061 0.5826 1.0000
7.500 0.3849 0.06853 0.05997 0.0060 0.5609 1.0000
7.750 0.3950 0.06963 0.06110 0.0067 0.5414 1.0000
8.000 0.4178 0.07030 0.06184 0.0071 0.5202 1.0000
8.250 0.4745 0.06890 0.06062 0.0076 0.4970 1.0000
8.500 0.4760 0.07045 0.06220 0.0085 0.4752 1.0000
8.750 0.5500 0.06599 0.05798 0.0106 0.4502 1.0000
9.250 0.7965 0.04039 0.03308 0.0205 0.3833 1.0000
9.500 0.8418 0.03686 0.02916 0.0235 0.3299 1.0000
9.750 0.8637 0.03688 0.02863 0.0256 0.2884 1.0000
10.000 0.8852 0.03814 0.02950 0.0268 0.2579 1.0000
10.250 0.8997 0.03989 0.03114 0.0279 0.2375 1.0000
10.500 0.9219 0.04170 0.03285 0.0283 0.2207 1.0000
10.750 0.9489 0.04385 0.03499 0.0281 0.2081 1.0000
11.000 0.9815 0.04600 0.03703 0.0274 0.1967 1.0000
11.250 0.9783 0.04848 0.03979 0.0294 0.1914 1.0000
11.500 1.0172 0.05095 0.04214 0.0280 0.1825 1.0000
11.750 1.0029 0.05389 0.04543 0.0306 0.1806 1.0000
12.000 0.9841 0.05724 0.04906 0.0327 0.1791 1.0000
12.250 0.9591 0.06129 0.05337 0.0341 0.1783 1.0000
12.500 0.9237 0.06658 0.05889 0.0343 0.1786 1.0000
12.750 0.8745 0.07403 0.06652 0.0327 0.1800 1.0000
13.000 0.8209 0.08394 0.07654 0.0290 0.1820 1.0000
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