NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 100,000 Max Cl/Cd: 44.54 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63209-il-100000-n5.txt Download as CSV file: xf-naca63209-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5673 0.08977 0.08480 -0.0177 1.0000 0.0289
-9.250 -0.5699 0.08449 0.07956 -0.0209 1.0000 0.0283
-9.000 -0.5755 0.07817 0.07330 -0.0257 1.0000 0.0279
-8.750 -0.5864 0.07165 0.06680 -0.0314 1.0000 0.0274
-8.500 -0.5994 0.06657 0.06167 -0.0347 1.0000 0.0270
-8.250 -0.6075 0.06153 0.05650 -0.0369 1.0000 0.0266
-8.000 -0.6114 0.05663 0.05139 -0.0383 1.0000 0.0262
-7.750 -0.6112 0.05181 0.04630 -0.0391 1.0000 0.0259
-7.500 -0.6066 0.04724 0.04139 -0.0393 1.0000 0.0257
-7.250 -0.5981 0.04301 0.03677 -0.0391 1.0000 0.0257
-7.000 -0.5862 0.03915 0.03248 -0.0386 1.0000 0.0259
-6.750 -0.5714 0.03575 0.02862 -0.0378 1.0000 0.0265
-6.500 -0.5538 0.03312 0.02554 -0.0370 1.0000 0.0284
-6.250 -0.5345 0.03080 0.02272 -0.0360 1.0000 0.0301
-6.000 -0.5143 0.02854 0.02003 -0.0349 1.0000 0.0307
-5.750 -0.4936 0.02650 0.01765 -0.0338 1.0000 0.0314
-5.500 -0.4734 0.02413 0.01506 -0.0328 1.0000 0.0326
-5.250 -0.4532 0.02278 0.01367 -0.0319 1.0000 0.0352
-5.000 -0.4325 0.02171 0.01248 -0.0308 1.0000 0.0383
-4.750 -0.4121 0.02052 0.01118 -0.0295 1.0000 0.0402
-4.500 -0.3922 0.01948 0.01005 -0.0281 1.0000 0.0421
-4.250 -0.3732 0.01848 0.00900 -0.0268 1.0000 0.0443
-4.000 -0.3543 0.01766 0.00816 -0.0257 1.0000 0.0490
-3.750 -0.3213 0.01690 0.00731 -0.0273 0.9939 0.0574
-3.500 -0.2855 0.01609 0.00644 -0.0294 0.9865 0.0705
-3.250 -0.2511 0.01497 0.00567 -0.0315 0.9789 0.1278
-3.000 -0.2221 0.01297 0.00523 -0.0333 0.9717 0.4642
-2.750 -0.1894 0.01264 0.00532 -0.0340 0.9645 0.5989
-2.500 -0.1624 0.01265 0.00566 -0.0328 0.9551 0.7004
-2.250 -0.1339 0.01277 0.00582 -0.0320 0.9464 0.7530
-2.000 -0.1019 0.01278 0.00572 -0.0324 0.9381 0.7734
-1.750 -0.0712 0.01275 0.00560 -0.0328 0.9285 0.7892
-1.500 -0.0389 0.01271 0.00547 -0.0334 0.9202 0.8032
-1.250 -0.0086 0.01268 0.00534 -0.0337 0.9106 0.8166
-1.000 0.0203 0.01265 0.00525 -0.0337 0.9005 0.8299
-0.750 0.0502 0.01261 0.00516 -0.0338 0.8915 0.8430
-0.500 0.0787 0.01258 0.00508 -0.0337 0.8816 0.8564
-0.250 0.1058 0.01255 0.00502 -0.0333 0.8710 0.8701
0.000 0.1337 0.01252 0.00497 -0.0330 0.8612 0.8840
0.250 0.1626 0.01247 0.00491 -0.0329 0.8520 0.8981
0.500 0.1908 0.01244 0.00489 -0.0328 0.8411 0.9130
0.750 0.2215 0.01240 0.00487 -0.0332 0.8310 0.9280
1.000 0.2553 0.01236 0.00483 -0.0342 0.8219 0.9426
1.250 0.2908 0.01233 0.00486 -0.0357 0.8112 0.9574
1.500 0.3283 0.01232 0.00489 -0.0378 0.8005 0.9726
1.750 0.3664 0.01230 0.00492 -0.0400 0.7900 0.9900
2.000 0.3950 0.01235 0.00502 -0.0403 0.7791 1.0000
2.250 0.4186 0.01246 0.00516 -0.0397 0.7669 1.0000
2.500 0.4434 0.01258 0.00532 -0.0392 0.7541 1.0000
2.750 0.4688 0.01269 0.00549 -0.0387 0.7404 1.0000
3.000 0.4945 0.01278 0.00566 -0.0381 0.7247 1.0000
3.250 0.5194 0.01284 0.00577 -0.0372 0.7029 1.0000
3.500 0.5431 0.01283 0.00573 -0.0358 0.6678 1.0000
3.750 0.5642 0.01286 0.00555 -0.0337 0.6013 1.0000
4.000 0.5857 0.01315 0.00557 -0.0320 0.5181 1.0000
4.250 0.6069 0.01372 0.00577 -0.0307 0.4178 1.0000
4.500 0.6196 0.01560 0.00641 -0.0289 0.1949 1.0000
4.750 0.6370 0.01733 0.00742 -0.0280 0.0872 1.0000
5.000 0.6588 0.01841 0.00838 -0.0273 0.0630 1.0000
5.250 0.6813 0.01936 0.00938 -0.0266 0.0527 1.0000
5.500 0.7025 0.02047 0.01057 -0.0258 0.0467 1.0000
5.750 0.7249 0.02141 0.01160 -0.0251 0.0408 1.0000
6.000 0.7458 0.02269 0.01290 -0.0243 0.0376 1.0000
6.250 0.7672 0.02433 0.01457 -0.0234 0.0357 1.0000
6.500 0.7913 0.02581 0.01620 -0.0227 0.0344 1.0000
6.750 0.8162 0.02756 0.01817 -0.0222 0.0331 1.0000
7.000 0.8408 0.02942 0.02026 -0.0216 0.0315 1.0000
7.250 0.8637 0.03106 0.02211 -0.0211 0.0291 1.0000
7.500 0.8855 0.03300 0.02427 -0.0206 0.0275 1.0000
7.750 0.9059 0.03557 0.02710 -0.0199 0.0266 1.0000
8.000 0.9234 0.03883 0.03069 -0.0191 0.0259 1.0000
8.250 0.9367 0.04284 0.03514 -0.0181 0.0255 1.0000
8.500 0.9472 0.04627 0.03904 -0.0167 0.0251 1.0000
8.750 0.9551 0.04927 0.04262 -0.0151 0.0243 1.0000
9.000 0.9579 0.05288 0.04672 -0.0136 0.0234 1.0000
9.250 0.9555 0.05686 0.05111 -0.0121 0.0227 1.0000
9.500 0.9479 0.06105 0.05563 -0.0109 0.0226 1.0000
9.750 0.9343 0.06500 0.05982 -0.0095 0.0226 1.0000
10.000 0.9167 0.06912 0.06412 -0.0090 0.0227 1.0000
10.250 0.8973 0.07394 0.06911 -0.0103 0.0228 1.0000
10.500 0.8781 0.07963 0.07493 -0.0133 0.0230 1.0000
10.750 0.8583 0.08666 0.08206 -0.0182 0.0233 1.0000
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Polar data table (+)
Polar graphs
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