N-9 (n9-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-9 (n9-il) Reynolds number: 200,000 Max Cl/Cd: 63.38 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n9-il-200000-n5.txt Download as CSV file: xf-n9-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-9
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4805 0.08687 0.08334 -0.0214 1.0000 0.0159
-9.750 -0.4841 0.08219 0.07871 -0.0240 1.0000 0.0158
-9.500 -0.4907 0.07744 0.07402 -0.0268 1.0000 0.0157
-9.250 -0.4945 0.07148 0.06810 -0.0322 1.0000 0.0156
-9.000 -0.4967 0.06448 0.06110 -0.0384 1.0000 0.0155
-8.750 -0.4990 0.05610 0.05263 -0.0443 1.0000 0.0155
-8.500 -0.5043 0.04455 0.04073 -0.0494 1.0000 0.0154
-8.250 -0.5102 0.03191 0.02718 -0.0513 1.0000 0.0159
-8.000 -0.4979 0.02712 0.02167 -0.0507 1.0000 0.0172
-7.750 -0.4805 0.02430 0.01822 -0.0496 1.0000 0.0184
-7.500 -0.4621 0.02238 0.01607 -0.0486 1.0000 0.0194
-7.250 -0.4336 0.02122 0.01472 -0.0492 0.9979 0.0206
-7.000 -0.4001 0.01993 0.01317 -0.0507 0.9948 0.0227
-6.750 -0.3673 0.01885 0.01176 -0.0518 0.9907 0.0255
-6.500 -0.3347 0.01743 0.01014 -0.0531 0.9871 0.0279
-6.250 -0.3025 0.01676 0.00938 -0.0542 0.9823 0.0310
-6.000 -0.2688 0.01607 0.00850 -0.0553 0.9777 0.0347
-5.750 -0.2373 0.01512 0.00749 -0.0562 0.9718 0.0381
-5.500 -0.2036 0.01462 0.00693 -0.0575 0.9666 0.0425
-5.250 -0.1716 0.01411 0.00629 -0.0583 0.9600 0.0459
-5.000 -0.1378 0.01349 0.00569 -0.0596 0.9543 0.0506
-4.750 -0.1049 0.01305 0.00520 -0.0606 0.9470 0.0548
-4.500 -0.0699 0.01261 0.00472 -0.0620 0.9408 0.0608
-4.250 -0.0361 0.01228 0.00438 -0.0632 0.9335 0.0708
-4.000 -0.0001 0.01194 0.00402 -0.0647 0.9259 0.0844
-3.750 0.0341 0.01164 0.00368 -0.0659 0.9150 0.0986
-3.500 0.0671 0.01135 0.00336 -0.0668 0.9027 0.1120
-3.000 0.1256 0.01072 0.00300 -0.0672 0.8738 0.1936
-2.750 0.1524 0.01036 0.00287 -0.0670 0.8573 0.2679
-2.500 0.1775 0.00980 0.00277 -0.0665 0.8380 0.4047
-2.250 0.2015 0.00931 0.00270 -0.0656 0.8142 0.5425
-2.000 0.2245 0.00886 0.00262 -0.0642 0.7902 0.6712
-1.750 0.2460 0.00843 0.00259 -0.0618 0.7708 0.8349
-1.250 0.3236 0.00838 0.00236 -0.0657 0.7363 1.0000
-1.000 0.3498 0.00849 0.00231 -0.0652 0.7211 1.0000
-0.750 0.3762 0.00862 0.00230 -0.0647 0.7076 1.0000
-0.500 0.4026 0.00875 0.00231 -0.0643 0.6939 1.0000
-0.250 0.4287 0.00890 0.00234 -0.0639 0.6776 1.0000
0.000 0.4549 0.00904 0.00238 -0.0634 0.6605 1.0000
0.250 0.4810 0.00918 0.00243 -0.0630 0.6418 1.0000
0.500 0.5069 0.00933 0.00248 -0.0625 0.6215 1.0000
0.750 0.5328 0.00948 0.00254 -0.0620 0.5989 1.0000
1.000 0.5586 0.00964 0.00262 -0.0616 0.5745 1.0000
1.250 0.5844 0.00981 0.00270 -0.0611 0.5472 1.0000
1.500 0.6097 0.01003 0.00279 -0.0606 0.5143 1.0000
1.750 0.6341 0.01032 0.00291 -0.0599 0.4715 1.0000
2.000 0.6578 0.01072 0.00306 -0.0592 0.4270 1.0000
2.250 0.6821 0.01110 0.00327 -0.0586 0.3947 1.0000
2.500 0.7070 0.01144 0.00351 -0.0582 0.3709 1.0000
3.000 0.7574 0.01209 0.00404 -0.0574 0.3336 1.0000
3.250 0.7827 0.01240 0.00432 -0.0571 0.3154 1.0000
3.500 0.8074 0.01277 0.00463 -0.0567 0.2930 1.0000
3.750 0.8322 0.01313 0.00493 -0.0563 0.2650 1.0000
4.000 0.8566 0.01355 0.00525 -0.0559 0.2292 1.0000
4.250 0.8779 0.01435 0.00569 -0.0551 0.1601 1.0000
4.500 0.8999 0.01511 0.00627 -0.0545 0.1327 1.0000
4.750 0.9230 0.01570 0.00683 -0.0539 0.1221 1.0000
5.000 0.9469 0.01618 0.00737 -0.0534 0.1162 1.0000
5.250 0.9701 0.01672 0.00795 -0.0528 0.1107 1.0000
5.500 0.9921 0.01739 0.00865 -0.0521 0.1055 1.0000
5.750 1.0158 0.01785 0.00923 -0.0516 0.1016 1.0000
6.000 1.0386 0.01840 0.00987 -0.0510 0.0974 1.0000
6.250 1.0592 0.01918 0.01062 -0.0502 0.0914 1.0000
6.500 1.0842 0.01943 0.01102 -0.0499 0.0843 1.0000
6.750 1.1060 0.02002 0.01163 -0.0493 0.0777 1.0000
7.000 1.1303 0.02033 0.01210 -0.0490 0.0711 1.0000
7.250 1.1530 0.02079 0.01259 -0.0485 0.0634 1.0000
7.500 1.1757 0.02125 0.01310 -0.0480 0.0536 1.0000
7.750 1.1964 0.02192 0.01376 -0.0473 0.0405 1.0000
8.000 1.2135 0.02298 0.01474 -0.0461 0.0270 1.0000
8.250 1.2294 0.02414 0.01595 -0.0447 0.0212 1.0000
8.500 1.2440 0.02541 0.01729 -0.0431 0.0184 1.0000
8.750 1.2589 0.02655 0.01860 -0.0415 0.0168 1.0000
9.000 1.2723 0.02777 0.01997 -0.0399 0.0153 1.0000
9.250 1.2826 0.02919 0.02151 -0.0380 0.0140 1.0000
9.500 1.2861 0.03090 0.02338 -0.0352 0.0130 1.0000
9.750 1.2913 0.03242 0.02505 -0.0326 0.0126 1.0000
10.000 1.2960 0.03403 0.02685 -0.0304 0.0122 1.0000
10.250 1.2991 0.03584 0.02884 -0.0283 0.0118 1.0000
10.500 1.3008 0.03789 0.03106 -0.0264 0.0115 1.0000
10.750 1.3013 0.04013 0.03349 -0.0249 0.0112 1.0000
11.000 1.3010 0.04259 0.03615 -0.0237 0.0108 1.0000
11.250 1.2996 0.04529 0.03902 -0.0229 0.0105 1.0000
11.500 1.2972 0.04826 0.04216 -0.0225 0.0102 1.0000
11.750 1.2936 0.05157 0.04562 -0.0226 0.0099 1.0000
12.000 1.2879 0.05531 0.04951 -0.0232 0.0097 1.0000
12.250 1.2805 0.05947 0.05384 -0.0241 0.0095 1.0000
12.500 1.2707 0.06414 0.05866 -0.0254 0.0093 1.0000
12.750 1.2594 0.06925 0.06393 -0.0271 0.0091 1.0000
13.000 1.2462 0.07484 0.06968 -0.0291 0.0090 1.0000
13.500 1.2196 0.08699 0.08217 -0.0344 0.0089 1.0000
13.750 1.2059 0.09364 0.08900 -0.0377 0.0089 1.0000
14.000 1.1915 0.10067 0.09621 -0.0413 0.0089 1.0000
14.250 1.1761 0.10818 0.10388 -0.0452 0.0089 1.0000
14.500 1.1603 0.11593 0.11177 -0.0492 0.0089 1.0000
14.750 1.1440 0.12409 0.12008 -0.0536 0.0089 1.0000
15.000 1.1278 0.13255 0.12867 -0.0582 0.0089 1.0000
15.250 1.1115 0.14154 0.13782 -0.0632 0.0090 1.0000
15.500 1.0927 0.15204 0.14848 -0.0690 0.0092 1.0000
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