NACA 1410 (naca1410-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 1410 (naca1410-il) Reynolds number: 500,000 Max Cl/Cd: 70.81 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1410-il-500000.txt Download as CSV file: xf-naca1410-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1410
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7901 0.10688 0.10456 -0.0001 1.0000 0.0169
-13.250 -1.0099 0.05267 0.04964 -0.0381 1.0000 0.0142
-13.000 -1.0303 0.04578 0.04250 -0.0436 1.0000 0.0142
-12.750 -1.0410 0.04173 0.03825 -0.0455 1.0000 0.0144
-12.500 -1.0487 0.03877 0.03510 -0.0452 1.0000 0.0146
-12.250 -1.0527 0.03656 0.03270 -0.0434 1.0000 0.0149
-12.000 -1.0513 0.03445 0.03038 -0.0418 1.0000 0.0153
-11.750 -1.0451 0.03245 0.02815 -0.0404 1.0000 0.0157
-11.500 -1.0352 0.03067 0.02614 -0.0390 1.0000 0.0161
-11.250 -1.0266 0.02847 0.02365 -0.0375 1.0000 0.0165
-11.000 -1.0175 0.02617 0.02116 -0.0359 1.0000 0.0173
-10.750 -0.9984 0.02542 0.02036 -0.0351 1.0000 0.0179
-10.500 -0.9783 0.02475 0.01962 -0.0343 1.0000 0.0186
-10.250 -0.9585 0.02397 0.01872 -0.0334 1.0000 0.0196
-10.000 -0.9380 0.02325 0.01786 -0.0325 1.0000 0.0206
-9.750 -0.9159 0.02285 0.01732 -0.0317 1.0000 0.0214
-9.500 -0.9014 0.02090 0.01526 -0.0302 1.0000 0.0228
-9.250 -0.8800 0.02043 0.01477 -0.0293 1.0000 0.0239
-9.000 -0.8587 0.01990 0.01417 -0.0283 1.0000 0.0252
-8.750 -0.8371 0.01943 0.01358 -0.0273 1.0000 0.0267
-8.500 -0.8156 0.01895 0.01298 -0.0262 1.0000 0.0279
-8.250 -0.7983 0.01758 0.01157 -0.0247 1.0000 0.0300
-8.000 -0.7768 0.01715 0.01112 -0.0237 1.0000 0.0316
-7.750 -0.7553 0.01670 0.01061 -0.0226 1.0000 0.0334
-7.500 -0.7331 0.01644 0.01027 -0.0215 1.0000 0.0348
-7.250 -0.7147 0.01527 0.00901 -0.0200 1.0000 0.0369
-7.000 -0.6942 0.01469 0.00842 -0.0188 1.0000 0.0388
-6.750 -0.6726 0.01431 0.00802 -0.0177 1.0000 0.0406
-6.500 -0.6509 0.01395 0.00761 -0.0165 1.0000 0.0425
-6.250 -0.6290 0.01363 0.00722 -0.0154 1.0000 0.0438
-6.000 -0.6080 0.01305 0.00659 -0.0142 1.0000 0.0453
-5.750 -0.5870 0.01242 0.00595 -0.0131 1.0000 0.0478
-5.500 -0.5648 0.01208 0.00559 -0.0121 1.0000 0.0499
-5.250 -0.5421 0.01179 0.00528 -0.0113 1.0000 0.0521
-5.000 -0.5072 0.01147 0.00491 -0.0129 0.9980 0.0544
-4.750 -0.4705 0.01098 0.00441 -0.0149 0.9956 0.0590
-4.500 -0.4335 0.01065 0.00410 -0.0170 0.9931 0.0654
-4.250 -0.3978 0.01020 0.00372 -0.0188 0.9897 0.0816
-4.000 -0.3612 0.00970 0.00342 -0.0209 0.9868 0.1198
-3.750 -0.3232 0.00930 0.00320 -0.0233 0.9847 0.1604
-3.500 -0.2893 0.00895 0.00300 -0.0247 0.9799 0.1997
-3.250 -0.2523 0.00859 0.00284 -0.0268 0.9766 0.2466
-3.000 -0.2139 0.00826 0.00267 -0.0293 0.9742 0.2922
-2.750 -0.1816 0.00793 0.00249 -0.0303 0.9682 0.3331
-2.500 -0.1487 0.00739 0.00235 -0.0315 0.9630 0.4281
-2.250 -0.1188 0.00711 0.00226 -0.0319 0.9554 0.4956
-2.000 -0.0879 0.00687 0.00214 -0.0324 0.9480 0.5351
-1.750 -0.0609 0.00664 0.00204 -0.0320 0.9372 0.5724
-1.500 -0.0341 0.00638 0.00196 -0.0315 0.9265 0.6201
-1.250 -0.0078 0.00616 0.00189 -0.0308 0.9147 0.6674
-1.000 0.0176 0.00597 0.00183 -0.0299 0.9011 0.7144
-0.750 0.0419 0.00577 0.00180 -0.0287 0.8856 0.7688
-0.500 0.0662 0.00564 0.00179 -0.0274 0.8683 0.8175
-0.250 0.0907 0.00556 0.00179 -0.0262 0.8500 0.8583
0.000 0.1156 0.00555 0.00181 -0.0249 0.8311 0.8953
0.250 0.1420 0.00560 0.00183 -0.0241 0.8116 0.9249
0.500 0.1710 0.00568 0.00186 -0.0238 0.7905 0.9475
0.750 0.2042 0.00580 0.00189 -0.0246 0.7676 0.9641
1.000 0.2395 0.00593 0.00192 -0.0259 0.7419 0.9761
1.250 0.2771 0.00608 0.00195 -0.0279 0.7134 0.9847
1.500 0.3177 0.00623 0.00198 -0.0305 0.6847 0.9901
1.750 0.3560 0.00639 0.00201 -0.0328 0.6547 0.9955
2.000 0.3945 0.00659 0.00203 -0.0351 0.6126 1.0000
2.250 0.4188 0.00676 0.00205 -0.0344 0.5771 1.0000
2.500 0.4433 0.00692 0.00209 -0.0338 0.5464 1.0000
2.750 0.4675 0.00710 0.00214 -0.0331 0.5138 1.0000
3.000 0.4916 0.00729 0.00222 -0.0324 0.4831 1.0000
3.250 0.5157 0.00750 0.00231 -0.0316 0.4510 1.0000
3.500 0.5395 0.00775 0.00241 -0.0309 0.4161 1.0000
3.750 0.5633 0.00801 0.00254 -0.0301 0.3822 1.0000
4.000 0.5870 0.00829 0.00269 -0.0293 0.3450 1.0000
4.250 0.6102 0.00865 0.00287 -0.0285 0.3021 1.0000
4.500 0.6329 0.00907 0.00309 -0.0277 0.2558 1.0000
4.750 0.6556 0.00953 0.00334 -0.0268 0.2101 1.0000
5.000 0.6781 0.01002 0.00363 -0.0259 0.1662 1.0000
5.250 0.7005 0.01058 0.00397 -0.0251 0.1229 1.0000
5.500 0.7224 0.01124 0.00440 -0.0241 0.0822 1.0000
5.750 0.7451 0.01183 0.00486 -0.0232 0.0632 1.0000
6.000 0.7694 0.01223 0.00528 -0.0226 0.0574 1.0000
6.250 0.7932 0.01268 0.00571 -0.0219 0.0530 1.0000
6.500 0.8160 0.01329 0.00635 -0.0210 0.0498 1.0000
6.750 0.8405 0.01367 0.00679 -0.0204 0.0482 1.0000
7.000 0.8646 0.01409 0.00725 -0.0197 0.0462 1.0000
7.250 0.8883 0.01456 0.00776 -0.0191 0.0442 1.0000
7.500 0.9107 0.01520 0.00840 -0.0182 0.0420 1.0000
7.750 0.9300 0.01625 0.00952 -0.0170 0.0399 1.0000
8.000 0.9543 0.01662 0.00995 -0.0164 0.0388 1.0000
8.250 0.9778 0.01710 0.01049 -0.0158 0.0371 1.0000
8.500 1.0008 0.01763 0.01108 -0.0151 0.0354 1.0000
8.750 1.0228 0.01824 0.01171 -0.0143 0.0336 1.0000
9.000 1.0387 0.01984 0.01337 -0.0128 0.0313 1.0000
9.250 1.0624 0.02017 0.01379 -0.0122 0.0303 1.0000
9.500 1.0846 0.02071 0.01441 -0.0114 0.0287 1.0000
9.750 1.1064 0.02122 0.01497 -0.0107 0.0270 1.0000
10.000 1.1258 0.02202 0.01578 -0.0097 0.0255 1.0000
10.250 1.1414 0.02350 0.01738 -0.0083 0.0240 1.0000
10.500 1.1621 0.02404 0.01803 -0.0074 0.0228 1.0000
10.750 1.1812 0.02473 0.01882 -0.0063 0.0216 1.0000
11.000 1.2001 0.02532 0.01946 -0.0053 0.0205 1.0000
11.250 1.2169 0.02607 0.02024 -0.0041 0.0196 1.0000
11.500 1.2253 0.02797 0.02227 -0.0020 0.0185 1.0000
11.750 1.2404 0.02867 0.02310 -0.0005 0.0179 1.0000
12.000 1.2512 0.02963 0.02420 0.0015 0.0171 1.0000
12.250 1.2605 0.03073 0.02541 0.0035 0.0165 1.0000
12.500 1.2694 0.03182 0.02659 0.0052 0.0159 1.0000
12.750 1.2777 0.03297 0.02781 0.0068 0.0155 1.0000
13.000 1.2838 0.03439 0.02932 0.0082 0.0150 1.0000
13.250 1.2835 0.03660 0.03163 0.0097 0.0146 1.0000
13.500 1.2713 0.04039 0.03564 0.0112 0.0142 1.0000
13.750 1.2688 0.04320 0.03865 0.0116 0.0140 1.0000
14.000 1.2663 0.04623 0.04187 0.0114 0.0138 1.0000
14.250 1.2610 0.04981 0.04564 0.0107 0.0136 1.0000
14.500 1.2533 0.05400 0.05001 0.0093 0.0134 1.0000
14.750 1.2432 0.05879 0.05500 0.0072 0.0133 1.0000
15.000 1.2307 0.06428 0.06066 0.0045 0.0131 1.0000
15.250 1.2147 0.07059 0.06716 0.0011 0.0130 1.0000
15.500 1.1940 0.07804 0.07479 -0.0031 0.0130 1.0000
15.750 1.1693 0.08658 0.08352 -0.0081 0.0130 1.0000
16.000 1.1366 0.09723 0.09438 -0.0143 0.0132 1.0000
16.250 1.0979 0.10978 0.10712 -0.0217 0.0135 1.0000
16.500 1.0416 0.12731 0.12485 -0.0318 0.0139 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 1410 (naca1410-il)